CN116296418A - Large-space flow field characteristic parameter testing method based on distributed cross section - Google Patents
Large-space flow field characteristic parameter testing method based on distributed cross section Download PDFInfo
- Publication number
- CN116296418A CN116296418A CN202210991354.1A CN202210991354A CN116296418A CN 116296418 A CN116296418 A CN 116296418A CN 202210991354 A CN202210991354 A CN 202210991354A CN 116296418 A CN116296418 A CN 116296418A
- Authority
- CN
- China
- Prior art keywords
- section
- measuring
- test
- measurement
- static pressure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 184
- 238000005259 measurement Methods 0.000 claims abstract description 121
- 238000002347 injection Methods 0.000 claims abstract description 11
- 239000007924 injection Substances 0.000 claims abstract description 11
- 238000013441 quality evaluation Methods 0.000 claims abstract description 10
- 230000003068 static effect Effects 0.000 claims description 80
- 239000000523 sample Substances 0.000 claims description 36
- 150000001875 compounds Chemical class 0.000 claims description 21
- 238000000034 method Methods 0.000 claims description 20
- 239000002131 composite material Substances 0.000 claims description 15
- 238000012545 processing Methods 0.000 claims description 15
- 238000004364 calculation method Methods 0.000 claims description 12
- 230000015654 memory Effects 0.000 claims description 11
- 238000003672 processing method Methods 0.000 claims description 8
- 239000002737 fuel gas Substances 0.000 claims description 6
- 239000007789 gas Substances 0.000 claims description 6
- 238000007689 inspection Methods 0.000 claims description 4
- NAWXUBYGYWOOIX-SFHVURJKSA-N (2s)-2-[[4-[2-(2,4-diaminoquinazolin-6-yl)ethyl]benzoyl]amino]-4-methylidenepentanedioic acid Chemical compound C1=CC2=NC(N)=NC(N)=C2C=C1CCC1=CC=C(C(=O)N[C@@H](CC(=C)C(O)=O)C(O)=O)C=C1 NAWXUBYGYWOOIX-SFHVURJKSA-N 0.000 claims description 3
- 238000009530 blood pressure measurement Methods 0.000 claims description 3
- 238000007405 data analysis Methods 0.000 claims description 3
- 230000030279 gene silencing Effects 0.000 claims description 3
- 238000010992 reflux Methods 0.000 claims description 3
- 230000003584 silencer Effects 0.000 claims description 3
- 238000010998 test method Methods 0.000 abstract 1
- 238000011156 evaluation Methods 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 238000004590 computer program Methods 0.000 description 2
- 238000013480 data collection Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000002452 interceptive effect Effects 0.000 description 2
- 230000002146 bilateral effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Of Engines (AREA)
Abstract
The utility model relates to a large space flow field characteristic parameter test method based on distributed cross section, have aeroengine test room aerodynamic characteristic parameter test, flow field quality evaluation function, through reasonable measurement cross section, measurement point arrangement, obtain parameters such as test room average velocity of flow, injection coefficient, pressure drop, pressure loss, speed field homogeneity, utilize limited measurement cross section, obtain whole test bed space flow field information under the prerequisite that does not interfere with the normal test of engine, solved aeroengine test bed aerodynamic flow field parameter's comprehensive measurement and test bed flow field quality evaluation problem.
Description
Technical Field
The disclosure relates to the technical field of quality evaluation of flow fields of engine test benches, in particular to a large-space flow field characteristic parameter testing method and device based on a distributed section, and a pneumatic characteristic parameter processing method and system.
Background
The engine test bed is a large-scale test facility for developing the test run of the whole engine, and main performance parameters of the engine are all required to be determined through the test run of the whole engine, so that the engine test bed has important significance for the development of aeroengines.
The flow field quality of the test bed is the characteristic quality of the test bed, is directly related to the air inlet and outlet design, structural characteristics, local detail processing factors and the like of the test bed, and once the test bed is built, the flow characteristics of the test bed are basically determined. The flow field quality of the test bed reflects the quality of design and construction of the test bed, has very important significance for carrying out flow field quality test and evaluation work on a newly built test bed or an on-use test bed assembled with engines of different types, and is related to the effectiveness and reliability of the test bed data of the subsequent engines.
The engine test bed is a very huge test facility, the cross section area of a test room can generally reach the order of 10m multiplied by 10m, and at present, a plurality of newly-built test beds suitable for large bypass ratio engines are provided, the cross section area of the test room is generally 12m multiplied by 12m, and the length is more than 50 m. The systems such as a movable frame, a static frame, a hanging frame, a lifting platform, a fixed platform, a crown block and the like are usually arranged in the test bed, and all the systems can influence the quality of the pneumatic flow field of the test bed. In addition, different air inlet and exhaust structures and processing on details can also influence the quality of the pneumatic flow field of the test bed. In the prior art, in the flow field test of an engine test workshop, a measurement scheme is designed aiming at a concerned parameter in most of local flow field measurement, so that characteristic parameters of the flow field test workshop cannot be acquired aiming at the whole test space, and the quality evaluation requirement of the flow field of an aeroengine test bench cannot be met.
Therefore, the pneumatic flow field quality of each test bed has certain difference, and whether the pneumatic flow field quality of the test bed meets the index requirement and how to comprehensively measure and evaluate the pneumatic flow field quality of the test bed is a problem to be solved in the technical field.
Disclosure of Invention
In order to solve the problems, the application provides a large-space flow field characteristic parameter testing method and device based on a distributed section, and a pneumatic characteristic parameter processing method and system.
In one aspect of the application, a method for testing characteristic parameters of a large-space flow field based on a distributed section is provided, which comprises the following steps:
determining a measured section position in a test shop;
presetting a measurement system, wherein the measurement system is configured on the measurement section according to preset configuration points;
presetting an acquisition system, connecting the measurement system with the acquisition system, and preparing to acquire data;
after testing system performance and reliability inspection, starting data analysis software, starting an engine, adjusting to a required working condition, starting to collect data, and inputting and storing the collected data into the data analysis software;
and stopping the engine, processing the acquired data by using the data analysis software to obtain pneumatic characteristic parameters, and evaluating the quality of the flow field of the turbojet fan aeroengine test bed based on the pneumatic characteristic parameters.
As an alternative embodiment of the present application, optionally, determining the measured cross-sectional position within the test shop includes:
4 measurement sections were arranged in a test plant:
0 measuring the section distance from the lip (4-9) of the air inlet channel of the engine, wherein D is the diameter of an air inlet flow tube of the engine;
1, the measurement section is an air inlet lip section;
9, the measurement section is the section of the tail nozzle of the engine;
9a is positioned in the exhaust funnel of the test room and is spaced from the front (1-2) m of the perforated diffuser.
As an optional embodiment of the present application, optionally, a measurement system is preset, and the measurement system is configured on the measurement section according to a preset configuration point, including a measurement section measuring point arrangement of 0:
the 0 measurement section is equally divided into 25 rectangles according to 5 multiplied by 5, each measuring point is positioned at the center of the rectangle, the interval l=1/5L between the measuring points, and L is the section width of the test room;
0 measuring section is provided with 25 measuring points, and each measuring point is provided with 1 flow velocity sensor and 1 total static pressure compound probe respectively;
the flow velocity sensor is used for measuring the wind velocity to obtain the average flow velocity of the test room; the total static pressure composite probe total pressure hole is used for measuring total pressure to obtain air inlet pressure loss of the test room; the total static pressure composite probe static pressure hole arranged in the core area of the 0 measurement section is used for static pressure measurement, and the static pressure of the air inlet section is obtained.
As an optional embodiment of the present application, optionally, a measurement system is preset, and the measurement system is configured on the measurement section according to a preset configuration point, including a 1-section measurement point arrangement:
1, measuring the height of a measuring point of a section is the height of the central axis of a test room;
1, arranging two measuring points which are bilaterally symmetrical in a measuring section, wherein the distance between the two measuring points and the side wall surface of a test workshop is c, and c= (0.8-1.2) m;
each measuring point is provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the lip temperature and judging the backflow of the fuel gas;
the static pressure end of the total static pressure compound probe is connected with the high-pressure end of the differential pressure acquisition system and is used for measuring differential pressure to obtain pressure drop between test vehicles.
As an optional embodiment of the present application, optionally, a measurement system is preset, and the measurement system is configured on the measurement section according to a preset configuration point, including 9 measurement section measurement point arrangements:
9, measuring the height of a measuring point of the section to be the height of the central axis of the test room;
9, arranging two measuring points with bilateral symmetry on the measuring section, wherein the distance between the two measuring points and the side wall surface of a test workshop is c, and c= (0.8-1.2) m;
each measuring point is provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the temperature of the tail nozzle and judging the backflow of the fuel gas;
the static pressure end of the total static pressure compound probe is connected with the low-pressure end of the differential pressure acquisition system and is used for measuring differential pressure to obtain pressure drop between test vehicles.
As an optional embodiment of the present application, optionally, presetting a measurement system, configuring the measurement system on the measurement section according to a preset configuration point includes 9a measurement section measurement point arrangement:
9a, the measuring section is positioned in an exhaust tube of a test room, three measuring points with equal distance are arranged along the diameter of the exhaust tube, s is s=1/3R (R is the radius of the exhaust tube), and the upper measuring point is equal to the axis of the engine in height;
each measuring point is respectively provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the temperature of the air flow and calculating the density;
the total static pressure composite probe measures static pressure and total-static pressure difference for density and flow rate calculation.
As an optional embodiment of the present application, optionally, presetting an acquisition system, connecting the measurement system with the acquisition system, preparing to acquire data, includes:
the flow velocity sensor, the total static pressure compound probe or the temperature sensor in each measuring section are correspondingly connected to a flow velocity acquisition system, a pressure acquisition system, a temperature acquisition system or a differential pressure acquisition system according to preset acquisition lines;
the static pressure end of the total static pressure composite probe in the measurement section 1 is connected with the high-pressure end of the differential pressure acquisition system;
and (3) accessing the static pressure end of the total static pressure composite probe in the 9-measurement section into the low-pressure end of the differential pressure acquisition system.
In another aspect of the present application, a device for implementing the method for testing a characteristic parameter of a large-space flow field based on a distributed cross section is provided, where the device includes:
measuring means for determining a measured cross-sectional position in the test shop;
the measuring system is arranged on the measuring device and is used for measuring and transmitting data on each measuring section;
the acquisition system is connected with the measurement system and is used for acquiring and transmitting measurement data transmitted by the measurement system;
the data analysis system is used for receiving and storing the acquired data input by the acquisition system, carrying out data processing on the acquired data to obtain pneumatic characteristic parameters, and realizing the quality evaluation of the test bed flow field of the turbojet fan aeroengine based on the pneumatic characteristic parameters.
In another aspect of the present application, a pneumatic characteristic parameter processing method based on the above-mentioned large-space flow field characteristic parameter testing method based on a distributed section is also provided, including the following steps:
1) Calculating the average flow rate in the air intake silencing device:
calculating the air inflow of the test room according to the formula (1)
Wherein:
ρ -test room air density, kg/m 3 ；
V 0,i -far the front section, the i-th measurement point speed, m/s.
A 0,i -far forward cross section, ith measurement point flow area, m 2 ；
Calculating the air density of the test room according to the formula (2):
wherein:
m-molar mass of air, g/mol;
T 0 ——atmospheric temperature, K;
r-general gas constant, 8.314J/(mol.K);
calculating the average flow rate in the intake silencer according to the formula (3):
wherein:
A J flow area of intake muffler device, m 2 ；
2) Calculating the average flow rate of the test workshop:
calculating the average flow rate of the test workshop according to the formula (4):
wherein:
V 0，1 -speed of the i-th measuring point of the far front section, m/s;
3) Calculating the central flow rate of the exhaust pipe:
calculating the central flow rate of the exhaust funnel according to the formula (5):
wherein:
ΔP-total static pressure difference in the exhaust stack, pa;
rho, local density of air flow in exhaust stack, kg/m 3 ；
4) Calculating the air inlet pressure loss of a test workshop:
calculating a total pressure average value according to a formula (6):
wherein:
P t0,i -far the front section, the total pressure value of the ith measuring point, pa;
the intake pressure loss is calculated according to the formula (7):
wherein:
P 0 atmospheric pressure, pa.
5) Pressure drop calculation in the test workshop:
the pressure drop between test runs is:
P s，d ＝P s1 -P s9 (8)
wherein:
P S1 the static pressure value Pa of the lip section is obtained by the static pressure average value of all measuring points of the lip section;
P S9 the static pressure value Pa of the section of the tail nozzle is obtained by the static pressure average value of all measuring points of the section of the tail nozzle;
6) And (3) calculating gas reflux:
calculating the inlet and outlet section temperature difference of the test workshop according to the formula (9):
ΔT＝T 9 -T 1 (9)
wherein:
DeltaT, temperature difference of air inlet and outlet sections of a workshop, and DEG C;
T 1 the temperature of the section of the air inlet lip is obtained by the average value of the temperatures of all the measuring points of the section of the lip;
T 9 the temperature of the section of the tail nozzle of the engine is obtained by the average value of the temperatures of all the measuring points of the section of the tail nozzle;
7) Injection coefficient calculation:
calculating the injection coefficient according to the formula (10)
Wherein:
W a -engine intake flow, kg/s;
8) And (3) calculating pneumatic load of a test workshop:
calculating the pneumatic load of the test room according to the formula (11):
P s，f ＝P s9 -P 0 (11)
9) Speed field uniformity calculation:
calculating the speed field uniformity of the core area of the test workshop according to the formula (12):
wherein:
V 0,max -maximum speed, m/s, far from the core region of the anterior section;
V 0,min -minimum velocity, m/s, far from the core region of the anterior cross section.
In another aspect of the present application, a pneumatic characteristic parameter processing system is further provided, including:
a processor;
a memory for storing processor-executable instructions;
wherein the processor is configured to implement the pneumatic characteristic parameter processing method described above when executing the executable instructions.
The invention has the technical effects that: the method has the functions of testing aerodynamic feature parameters of the test room of the aeroengine and evaluating the quality of the flow field, obtains parameters such as average flow velocity, injection coefficient, pressure drop, pressure loss, uniformity of a speed field and the like of the test room through reasonable measurement section and measuring point arrangement, obtains the spatial flow field information of the whole test bed by utilizing the limited measurement section on the premise of not interfering with normal test of the engine, and solves the problems of comprehensive measurement of the aerodynamic flow field parameters of the test bed of the aeroengine and evaluating the quality of the flow field of the test bed.
Other features and aspects of the present disclosure will become apparent from the following detailed description of exemplary embodiments, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments, features and aspects of the present disclosure and together with the description, serve to explain the principles of the disclosure.
FIG. 1 is a schematic diagram of an implementation flow of a large-space flow field characteristic parameter testing method based on a distributed section;
FIG. 2 is a schematic diagram of a distributed cross-sectional arrangement of the present invention;
FIG. 3 is a 0-section station layout of the present invention;
FIG. 4 is a 1-section and 9-section station layout of the present invention;
FIG. 5 is a 9a cross-sectional station layout of the present invention;
fig. 6 is a layout of the acquisition system of the present invention.
Detailed Description
Various exemplary embodiments, features and aspects of the disclosure will be described in detail below with reference to the drawings. In the drawings, like reference numbers indicate identical or functionally similar elements. Although various aspects of the embodiments are illustrated in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
The word "exemplary" is used herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments.
In addition, numerous specific details are set forth in the following detailed description in order to provide a better understanding of the present disclosure. It will be understood by those skilled in the art that the present disclosure may be practiced without some of these specific details. In some instances, methods, means, elements, and circuits well known to those skilled in the art have not been described in detail in order not to obscure the present disclosure.
For a detailed description of the present invention, some concepts are defined below.
Definition one: intake pressure loss: the pressure loss caused by the air inlet system of the test bed of the engine is characterized by the difference between the local atmospheric pressure outside the test bed and the total pressure inside the test bed.
Definition two: pressure drop between test runs: in the test shop, static pressure differences of the section 1 and the section 9 of the engine are obtained.
Definition three: injection coefficient: in the test plant, the ratio of bypass airflow to engine intake airflow was calculated.
Definition four: core area of test room: in the test plant, a 0-section airflow flowed into the area within the engine.
Definition five: speed field uniformity in the core area of the test workshop: the ratio of the difference between the maximum value and the minimum value of the air flow velocity in the core area of the test room to the velocity average value.
Example 1
The method and the device have the advantages that parameters such as average flow velocity, injection coefficient, pressure drop, pressure loss, speed field uniformity and the like of a test room are obtained through reasonable measurement cross section and measurement point arrangement, the space flow field information of the whole test bed is obtained on the premise that normal test of an engine is not interfered by utilizing limited measurement cross sections, and the problems of comprehensive measurement of pneumatic flow field parameters of the test bed of an aeroengine and quality evaluation of the flow field of the test bed are solved.
As shown in fig. 1, in one aspect, the present application provides a method for testing a characteristic parameter of a large-space flow field based on a distributed section, which includes the following steps:
determining a measured section position in a test shop;
presetting a measurement system, wherein the measurement system is configured on the measurement section according to preset configuration points;
presetting an acquisition system, connecting the measurement system with the acquisition system, and preparing to acquire data;
after testing system performance and reliability inspection, starting data analysis software, starting an engine, adjusting to a required working condition, starting to collect data, and inputting and storing the collected data into the data analysis software;
and stopping the engine, processing the acquired data by using the data analysis software to obtain pneumatic characteristic parameters, and evaluating the quality of the flow field of the turbojet fan aeroengine test bed based on the pneumatic characteristic parameters.
The measurement systems on the measurement sections are installed according to the connection lines set by the user, and can be connected in a connection mode shown in fig. 6.
The implementation method and steps of each step will be specifically described below.
As shown in fig. 2, as an alternative embodiment of the present application, optionally, determining the measured cross-sectional position within the test shop includes:
4 measurement sections were arranged in a test plant:
0 measuring the section distance from the lip (4-9) of the air inlet channel of the engine, wherein D is the diameter of an air inlet flow tube of the engine;
1, the measurement section is an air inlet lip section;
9, the measurement section is the section of the tail nozzle of the engine;
9a is positioned in the exhaust funnel of the test room and is spaced from the front (1-2) m of the perforated diffuser.
As shown in fig. 3, as an alternative embodiment of the present application, optionally, a measurement system is preset, and the measurement system is configured on the measurement section according to a preset configuration point, including a measurement section measurement point arrangement of 0:
the 0 measurement section is equally divided into 25 rectangles according to 5 multiplied by 5, each measuring point is positioned at the center of the rectangle, the interval l=1/5L between the measuring points, and L is the section width of the test room;
0 measuring section is provided with 25 measuring points, and each measuring point is provided with 1 flow velocity sensor and 1 total static pressure compound probe respectively;
the flow velocity sensor is used for measuring the wind velocity to obtain the average flow velocity of the test room; the total static pressure composite probe total pressure hole is used for measuring total pressure to obtain air inlet pressure loss of the test room; the total static pressure composite probe static pressure hole arranged in the core area of the 0 measurement section is used for static pressure measurement, and the static pressure of the air inlet section is obtained.
As shown in fig. 4, as an alternative embodiment of the present application, optionally, a measurement system is preset, and the measurement system is configured on the measurement section according to a preset configuration point, including a 1-section measurement point arrangement:
1, measuring the height of a measuring point of a section is the height of the central axis of a test room;
1, arranging two measuring points 26 and 27 which are bilaterally symmetrical in a measuring section, wherein the distances between the two measuring points and the side wall surface of a test workshop are c, and c= (0.8-1.2) m;
each measuring point is provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the lip temperature and judging the backflow of the fuel gas;
the static pressure end of the total static pressure compound probe is connected with the high-pressure end of the differential pressure acquisition system and is used for measuring differential pressure to obtain pressure drop between test vehicles.
As shown in fig. 4 and 5, as an alternative embodiment of the present application, optionally, a measurement system is preset, and the measurement system is configured on the measurement section according to a preset configuration point, including a 9 measurement section measurement point arrangement:
9, measuring the height of a measuring point of the section to be the height of the central axis of the test room;
9, arranging two measuring points 28 and 29 which are bilaterally symmetrical in the measuring section, wherein the distances between the two measuring points and the side wall surface of a test workshop are c, and c= (0.8-1.2) m;
each measuring point is provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the temperature of the tail nozzle and judging the backflow of the fuel gas;
the static pressure end of the total static pressure compound probe is connected with the low-pressure end of the differential pressure acquisition system and is used for measuring differential pressure to obtain pressure drop between test vehicles.
As shown in fig. 5, as an alternative embodiment of the present application, optionally, a measurement system is preset, and the measurement system is configured on the measurement section according to a preset configuration point, including a 9a measurement section measurement point arrangement:
9a measuring section is positioned in an exhaust tube of the test room, and three measuring points with equal distance are arranged along the diameter of the exhaust tube: the measuring point 30, the measuring point 31 and the measuring point 32 are s, s=1/3R (R is the radius of the exhaust pipe), and the measuring point 32 at the upper part is equal to the axis of the engine in height;
each measuring point is respectively provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the temperature of the air flow and calculating the density;
the total static pressure composite probe measures static pressure and total-static pressure difference for density and flow rate calculation.
As shown in fig. 6, as an alternative embodiment of the present application, optionally, a collection system is preset, the measurement system is connected with the collection system, and data collection is prepared, including:
the flow velocity sensor, the total static pressure compound probe or the temperature sensor in each measuring section are correspondingly connected to a flow velocity acquisition system, a pressure acquisition system, a temperature acquisition system or a differential pressure acquisition system according to preset acquisition lines;
the static pressure end of the total static pressure composite probe in the measurement section 1 is connected with the high-pressure end of the differential pressure acquisition system;
and (3) accessing the static pressure end of the total static pressure composite probe in the 9-measurement section into the low-pressure end of the differential pressure acquisition system.
After the acquisition system of each section is configured/installed, checking the performance and reliability of the test system;
starting data analysis software after the inspection is finished, starting an engine, adjusting to a required working condition, and storing data acquired by sensors of all measuring points of each working condition into the software;
and the engine is stopped, the acquired data is processed by utilizing data analysis software, and pneumatic characteristic parameters are obtained, so that the quality of the flow field of the turbojet fan aeroengine test bed is evaluated.
The evaluation requirements for aerodynamic feature parameters are shown in table 1 below:
TABLE 1 evaluation requirements of aerodynamic parameters
Therefore, the large-space flow field characteristic parameter testing method based on the distributed section has the functions of aeroengine test room aerodynamic characteristic parameter testing and flow field quality evaluation, and parameters such as average flow velocity, injection coefficient, pressure drop, pressure loss, speed field uniformity and the like of the test room are obtained through reasonable measurement section and measuring point arrangement, the whole test bed space flow field information is obtained on the premise of not interfering with normal test of the engine by utilizing the limited measurement section, and the problems of comprehensive measurement of aeroengine test bed aerodynamic flow field parameters and test bed flow field quality evaluation are solved.
In this embodiment, each collection system/device, and the data collection system, and the data analysis software, there are testers to select according to the requirements, and this embodiment is not limited.
Example 2
Based on the implementation principle of embodiment 1, another aspect of the present application proposes an apparatus for implementing the above-mentioned method for testing a large-space flow field characteristic parameter based on a distributed cross section, where the apparatus includes:
measuring means for determining a measured cross-sectional position in the test shop;
the measuring system is arranged on the measuring device and is used for measuring and transmitting data on each measuring section;
the acquisition system is connected with the measurement system and is used for acquiring and transmitting measurement data transmitted by the measurement system;
the data analysis system is used for receiving and storing the acquired data input by the acquisition system, carrying out data processing on the acquired data to obtain pneumatic characteristic parameters, and realizing the quality evaluation of the test bed flow field of the turbojet fan aeroengine based on the pneumatic characteristic parameters.
The specific arrangement structure of each system or device described above, and description of embodiment 1 will not be repeated.
Example 3
In another aspect of the present application, a pneumatic characteristic parameter processing method based on the large-space flow field characteristic parameter testing method based on the distributed section described in the above embodiment 1 is further provided, including the following steps:
1) Calculating the average flow rate in the air intake silencing device:
calculating the air inflow of the test room according to the formula (1)
Wherein:
ρ -test room air density, kg/m 3 ；
V 0,i ——Far front section, i-th measuring point speed, m/s.
A 0,i -far forward cross section, ith measurement point flow area, m 2 ；
Calculating the air density of the test room according to the formula (2):
wherein:
m-molar mass of air, g/mol;
T 0 -atmospheric temperature, K;
r-general gas constant, 8.314J/(mol.K);
calculating the average flow rate in the intake silencer according to the formula (3):
wherein:
A J flow area of intake muffler device, m 2 ；
2) Calculating the average flow rate of the test workshop:
calculating the average flow rate of the test workshop according to the formula (4):
wherein:
V 0，1 -speed of the i-th measuring point of the far front section, m/s;
3) Calculating the central flow rate of the exhaust pipe:
calculating the central flow rate of the exhaust funnel according to the formula (5):
wherein:
ΔP-total static pressure difference in the exhaust stack, pa;
rho, local density of air flow in exhaust stack, kg/m 3 ；
4) Calculating the air inlet pressure loss of a test workshop:
calculating a total pressure average value according to a formula (6):
wherein:
P t0,i -far the front section, the total pressure value of the ith measuring point, pa;
the intake pressure loss is calculated according to the formula (7):
wherein:
P 0 atmospheric pressure, pa.
5) Pressure drop calculation in the test workshop:
the pressure drop between test runs is:
P s，d ＝P s1 -P s9 (8)
wherein:
P S1 the static pressure value Pa of the lip section is obtained by the static pressure average value of all measuring points of the lip section;
P S9 the static pressure value Pa of the section of the tail nozzle is obtained by the static pressure average value of all measuring points of the section of the tail nozzle;
6) And (3) calculating gas reflux:
calculating the inlet and outlet section temperature difference of the test workshop according to the formula (9):
ΔT＝T 9 -T 1 (9)
wherein:
DeltaT, temperature difference of air inlet and outlet sections of a workshop, and DEG C;
T 1 the temperature of the section of the air inlet lip is obtained by the average value of the temperatures of all the measuring points of the section of the lip;
T 9 the temperature of the section of the tail nozzle of the engine is obtained by the average value of the temperatures of all the measuring points of the section of the tail nozzle;
7) Injection coefficient calculation:
calculating the injection coefficient according to the formula (10)
Wherein:
W a -engine intake flow, kg/s;
8) And (3) calculating pneumatic load of a test workshop:
calculating the pneumatic load of the test room according to the formula (11):
P s，f ＝P s9 -P 0 (11)
9) Speed field uniformity calculation:
calculating the speed field uniformity of the core area of the test workshop according to the formula (12):
wherein:
V 0,max -maximum speed, m/s, far from the core region of the anterior section;
V 0,min -minimum velocity, m/s, far from the core region of the anterior cross section.
The parameters required by the above formulas are obtained according to the method provided in embodiment 1, and detailed details are not repeated in this embodiment.
It should be apparent to those skilled in the art that the implementation of all or part of the above-described embodiments of the method may be implemented by a computer program for instructing relevant hardware, and the program may be stored in a computer readable storage medium, and the program may include the steps of the embodiments of the control methods described above when executed. The modules or steps of the invention described above may be implemented in a general-purpose computing device, they may be centralized in a single computing device, or distributed across a network of computing devices, or they may alternatively be implemented in program code executable by a computing device, such that they may be stored in a memory device and executed by a computing device, or they may be separately fabricated into individual integrated circuit modules, or multiple modules or steps within them may be fabricated into a single integrated circuit module. Thus, the present invention is not limited to any specific combination of hardware and software.
It will be appreciated by those skilled in the art that implementing all or part of the above-described embodiment methods may be implemented by a computer program for instructing relevant hardware, and the program may be stored in a computer readable storage medium, and the program may include the embodiment flow of each control method as described above when executed. The storage medium may be a magnetic disk, an optical disc, a Read-only memory (ROM), a random access memory (RandomAccessMemory, RAM), a flash memory (flash memory), a hard disk (HDD), or a Solid State Drive (SSD); the storage medium may also comprise a combination of memories of the kind described above.
Example 4
Still further, another aspect of the present application provides a pneumatic characteristic parameter processing system, including:
a processor;
a memory for storing processor-executable instructions;
wherein the processor is configured to implement the pneumatic characteristic parameter processing method described in embodiment 3 above when executing the executable instructions.
Embodiments of the present disclosure provide for a pneumatic characteristic parameter processing system that includes a processor and a memory for storing processor-executable instructions. The processor is configured to execute the executable instructions to implement any one of the above-described large-space flow field characteristic parameter testing methods based on the distributed cross section.
Here, it should be noted that the number of processors may be one or more. Meanwhile, in the pneumatic characteristic parameter processing system of the embodiment of the disclosure, an input device and an output device may be further included. The processor, the memory, the input device, and the output device may be connected by a bus, or may be connected by other means, which is not specifically limited herein.
The memory is a computer-readable storage medium that can be used to store software programs, computer-executable programs, and various modules, such as: the embodiment of the disclosure relates to a program or a module corresponding to a large-space flow field characteristic parameter testing method based on a distributed section. The processor executes various functional applications and data processing of the pneumatic characteristic parameter processing system by running software programs or modules stored in the memory.
The input device may be used to receive an input number or signal. Wherein the signal may be a key signal generated in connection with user settings of the device/terminal/server and function control. The output means may comprise a display device such as a display screen.
The foregoing description of the embodiments of the present disclosure has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described. The terminology used herein was chosen in order to best explain the principles of the embodiments, the practical application, or the technical improvement of the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.
Claims (10)
1. The large-space flow field characteristic parameter testing method based on the distributed section is characterized by comprising the following steps of:
determining a measured section position in a test shop;
presetting a measurement system, wherein the measurement system is configured on the measurement section according to preset configuration points;
presetting an acquisition system, connecting the measurement system with the acquisition system, and preparing to acquire data;
after testing system performance and reliability inspection, starting data analysis software, starting an engine, adjusting to a required working condition, starting to collect data, and inputting and storing the collected data into the data analysis software;
and stopping the engine, processing the acquired data by using the data analysis software to obtain pneumatic characteristic parameters, and evaluating the quality of the flow field of the turbojet fan aeroengine test bed based on the pneumatic characteristic parameters.
2. The distributed cross section based large space flow field feature parameter testing method of claim 1, wherein determining measured cross section locations within a test shop comprises:
4 measurement sections were arranged in a test plant:
0 measuring the section distance from the lip (4-9) of the air inlet channel of the engine, wherein D is the diameter of an air inlet flow tube of the engine;
1, the measurement section is an air inlet lip section;
9, the measurement section is the section of the tail nozzle of the engine;
9a is positioned in the exhaust funnel of the test room and is spaced from the front (1-2) m of the perforated diffuser.
3. The large-space flow field characteristic parameter testing method based on the distributed section according to claim 2, wherein a measurement system is preset, the measurement system is configured on the measurement section according to a preset configuration point, and the method comprises the following steps of 0 measurement section measuring point arrangement:
the 0 measurement section is equally divided into 25 rectangles according to 5 multiplied by 5, each measuring point is positioned at the center of the rectangle, the interval l=1/5L between the measuring points, and L is the section width of the test room;
0 measuring section is provided with 25 measuring points, and each measuring point is provided with 1 flow velocity sensor and 1 total static pressure compound probe respectively;
the flow velocity sensor is used for measuring the wind velocity to obtain the average flow velocity of the test room; the total static pressure composite probe total pressure hole is used for measuring total pressure to obtain air inlet pressure loss of the test room; the total static pressure composite probe static pressure hole arranged in the core area of the 0 measurement section is used for static pressure measurement, and the static pressure of the air inlet section is obtained.
4. The large-space flow field characteristic parameter testing method based on the distributed section according to claim 2, wherein a measurement system is preset, the measurement system is configured on the measurement section according to a preset configuration point, and the method comprises the following steps of 1-section measuring point arrangement:
1, measuring the height of a measuring point of a section is the height of the central axis of a test room;
1, arranging two measuring points (26) and two measuring points (27) which are bilaterally symmetrical in a measuring section, wherein the distances between the two measuring points and the side wall surface of a test workshop are c, and c= (0.8-1.2) m;
each measuring point is provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the lip temperature and judging the backflow of the fuel gas;
the static pressure end of the total static pressure compound probe is connected with the high-pressure end of the differential pressure acquisition system and is used for measuring differential pressure to obtain pressure drop between test vehicles.
5. The large-space flow field characteristic parameter testing method based on the distributed section according to claim 2, wherein a measurement system is preset, the measurement system is configured on the measurement section according to a preset configuration point, and the method comprises the steps of 9 measurement section measuring point arrangement:
9, measuring the height of a measuring point of the section to be the height of the central axis of the test room;
9, arranging two measuring points (28) and two measuring points (29) which are bilaterally symmetrical in the measuring section, wherein the distances between the two measuring points and the side wall surface of a test workshop are c, and c= (0.8-1.2) m;
each measuring point is provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the temperature of the tail nozzle and judging the backflow of the fuel gas;
the static pressure end of the total static pressure compound probe is connected with the low-pressure end of the differential pressure acquisition system and is used for measuring differential pressure to obtain pressure drop between test vehicles.
6. The large-space flow field characteristic parameter testing method based on the distributed section according to claim 2, wherein a measurement system is preset, the measurement system is configured on the measurement section according to a preset configuration point, and the method comprises the steps of 9a measurement section measuring point arrangement:
9a measuring section is positioned in an exhaust tube of the test room, and three measuring points with equal distance are arranged along the diameter of the exhaust tube: the measuring point (30), the measuring point (31) and the measuring point (32) are s, s=1/3R (R is the radius of the exhaust pipe), and the upper measuring point (measuring point 32) is equal to the axis of the engine in height;
each measuring point is respectively provided with 1 temperature sensor and 1 total static pressure compound probe;
the temperature sensor is used for measuring the temperature of the air flow and calculating the density;
the total static pressure composite probe measures static pressure and total-static pressure difference for density and flow rate calculation.
7. The method for testing the characteristic parameters of the large-space flow field based on the distributed cross section according to claim 2, wherein an acquisition system is preset, the measurement system is connected with the acquisition system, and data acquisition is prepared, and the method comprises the following steps:
the flow velocity sensor, the total static pressure compound probe or the temperature sensor in each measuring section are correspondingly connected to a flow velocity acquisition system, a pressure acquisition system, a temperature acquisition system or a differential pressure acquisition system according to preset acquisition lines;
the static pressure end of the total static pressure composite probe in the measurement section 1 is connected with the high-pressure end of the differential pressure acquisition system;
and (3) accessing the static pressure end of the total static pressure composite probe in the 9-measurement section into the low-pressure end of the differential pressure acquisition system.
8. An apparatus for implementing the distributed cross-section based large space flow field feature parameter testing method of any one of claims 1-7, comprising:
measuring means for determining a measured cross-sectional position in the test shop;
the measuring system is arranged on the measuring device and is used for measuring and transmitting data on each measuring section;
the acquisition system is connected with the measurement system and is used for acquiring and transmitting measurement data transmitted by the measurement system;
the data analysis system is used for receiving and storing the acquired data input by the acquisition system, carrying out data processing on the acquired data to obtain pneumatic characteristic parameters, and realizing the quality evaluation of the test bed flow field of the turbojet fan aeroengine based on the pneumatic characteristic parameters.
9. A pneumatic characteristic parameter processing method based on the large-space flow field characteristic parameter testing method based on the distributed section according to any one of claims 1 to 7, characterized by comprising the following steps:
1) Calculating the average flow rate in the air intake silencing device:
calculating the air inflow of the test room according to the formula (1)
Wherein:
ρ -test room air density, kg/m 3 ；
V 0,i -far the front section, the i-th measurement point speed, m/s.
A 0,i -far forward cross section, ith measurement point flow area, m 2 The method comprises the steps of carrying out a first treatment on the surface of the Calculating the air density of the test room according to the formula (2):
wherein:
T 0 -atmospheric temperature, K;
r-general gas constant, 8.314J/(mol.K);
calculating the average flow rate in the intake silencer according to the formula (3):
wherein:
A J flow area of intake muffler device, m 2 ；
2) Calculating the average flow rate of the test workshop:
calculating the average flow rate of the test workshop according to the formula (4):
wherein:
V 0，1 -speed of the i-th measuring point of the far front section, m/s;
3) Calculating the central flow rate of the exhaust pipe:
calculating the central flow rate of the exhaust funnel according to the formula (5):
wherein:
ΔP-total static pressure difference in the exhaust stack, pa;
ρ' -local density of air flow in exhaust stack, kg/m 3 ；
4) Calculating the air inlet pressure loss of a test workshop:
calculating a total pressure average value according to a formula (6):
wherein:
P t0,i -far the front section, the total pressure value at the ith measurement point，Pa；
The intake pressure loss is calculated according to the formula (7):
wherein:
P 0 atmospheric pressure, pa.
5) Pressure drop calculation in the test workshop:
the pressure drop between test runs is:
P s，d ＝P s1 -P s9 (8)
wherein:
P S1 the static pressure value Pa of the lip section is obtained by the static pressure average value of all measuring points of the lip section;
P S9 the static pressure value Pa of the section of the tail nozzle is obtained by the static pressure average value of all measuring points of the section of the tail nozzle;
6) And (3) calculating gas reflux:
calculating the inlet and outlet section temperature difference of the test workshop according to the formula (9):
ΔT＝T 9 -T 1 (9)
wherein:
DeltaT, temperature difference of air inlet and outlet sections of a workshop, and DEG C;
T 1 the temperature of the section of the air inlet lip is obtained by the average value of the temperatures of all the measuring points of the section of the lip;
T 9 the temperature of the section of the tail nozzle of the engine is obtained by the average value of the temperatures of all the measuring points of the section of the tail nozzle;
7) Injection coefficient calculation:
calculating the injection coefficient according to the formula (10)
Wherein:
W a -engine intake flow, kg/s;
8) And (3) calculating pneumatic load of a test workshop:
calculating the pneumatic load of the test room according to the formula (11):
P s，f ＝P s9 -P 0 (11)
9) Speed field uniformity calculation:
calculating the speed field uniformity of the core area of the test workshop according to the formula (12):
wherein:
V 0,max -maximum speed, m/s, far from the core region of the anterior section;
V 0,min -minimum velocity, m/s, far from the core region of the anterior cross section.
10. A pneumatic characteristic parameter processing system, comprising:
a processor;
a memory for storing processor-executable instructions;
wherein the processor is configured to implement the pneumatic characteristic parameter processing method of claim 9 when executing the executable instructions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210991354.1A CN116296418B (en) | 2022-08-18 | 2022-08-18 | Large-space flow field characteristic parameter testing method based on distributed cross section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210991354.1A CN116296418B (en) | 2022-08-18 | 2022-08-18 | Large-space flow field characteristic parameter testing method based on distributed cross section |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116296418A true CN116296418A (en) | 2023-06-23 |
| CN116296418B CN116296418B (en) | 2024-01-16 |
Family
ID=86785617
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210991354.1A Active CN116296418B (en) | 2022-08-18 | 2022-08-18 | Large-space flow field characteristic parameter testing method based on distributed cross section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116296418B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117113887A (en) * | 2023-10-24 | 2023-11-24 | 中国航空工业集团公司北京长城计量测试技术研究所 | Method and device for correcting additional resistance of air inlet channel of indoor test bed of aero-engine |
| CN117541640A (en) * | 2024-01-09 | 2024-02-09 | 西南科技大学 | Method, equipment and medium for judging uniformity of aerodynamic flow field of cascade test oil flow diagram |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4537066A (en) * | 1982-11-10 | 1985-08-27 | Rolls-Royce Limited | Aeroengine test cells |
| CN102053017A (en) * | 2009-11-09 | 2011-05-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and system for testing air flow field of indoor engine test-bed |
| US20170002821A1 (en) * | 2014-03-18 | 2017-01-05 | Siemens Energy, Inc. | System for measuring air mass flow into a gas turbine |
| CN110455544A (en) * | 2019-08-29 | 2019-11-15 | 中国航空工业集团公司北京长城计量测试技术研究所 | Engine testsand inlet flow field based on fixed measuring point monitors system and method |
-
2022
- 2022-08-18 CN CN202210991354.1A patent/CN116296418B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4537066A (en) * | 1982-11-10 | 1985-08-27 | Rolls-Royce Limited | Aeroengine test cells |
| CN102053017A (en) * | 2009-11-09 | 2011-05-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and system for testing air flow field of indoor engine test-bed |
| US20170002821A1 (en) * | 2014-03-18 | 2017-01-05 | Siemens Energy, Inc. | System for measuring air mass flow into a gas turbine |
| CN110455544A (en) * | 2019-08-29 | 2019-11-15 | 中国航空工业集团公司北京长城计量测试技术研究所 | Engine testsand inlet flow field based on fixed measuring point monitors system and method |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117113887A (en) * | 2023-10-24 | 2023-11-24 | 中国航空工业集团公司北京长城计量测试技术研究所 | Method and device for correcting additional resistance of air inlet channel of indoor test bed of aero-engine |
| CN117113887B (en) * | 2023-10-24 | 2024-01-23 | 中国航空工业集团公司北京长城计量测试技术研究所 | Method and device for correcting additional resistance of air inlet channel of indoor test bed of aero-engine |
| CN117541640A (en) * | 2024-01-09 | 2024-02-09 | 西南科技大学 | Method, equipment and medium for judging uniformity of aerodynamic flow field of cascade test oil flow diagram |
| CN117541640B (en) * | 2024-01-09 | 2024-04-02 | 西南科技大学 | Method, equipment and medium for judging uniformity of aerodynamic flow field of cascade test oil flow diagram |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116296418B (en) | 2024-01-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN116296418B (en) | Large-space flow field characteristic parameter testing method based on distributed cross section | |
| US10788399B2 (en) | Apparatus for evaluating turbine engine system stability | |
| Arts et al. | Aero-thermal performance of a two-dimensional highly loaded transonic turbine nozzle guide vane: A test case for inviscid and viscous flow computations | |
| CN102053017B (en) | Method and system for testing air flow field of indoor engine test-bed | |
| CN111044252B (en) | High-precision air inlet channel flow measuring method | |
| CN104345118B (en) | Solid propellant many targets line Dynamic Burning Performance Test System and method | |
| US20140208764A1 (en) | Systems and methods for measuring a flow profile in a turbine engine flow path | |
| CN106383035A (en) | Muffler transmission loss testing system and muffler transmission loss testing method for aiming at aerodynamic noise | |
| US20140208755A1 (en) | Gas Turbine Air Mass Flow Measuring System and Methods for Measuring Air Mass Flow in a Gas Turbine Inlet Duct | |
| US4537066A (en) | Aeroengine test cells | |
| CN110455544B (en) | Engine test bed air inlet flow field monitoring system and method based on fixed measuring points | |
| CN106845083B (en) | A method of it calculating SCR catalytic muffler transient cycle and tests brake specific emission | |
| CN114152445A (en) | Total pressure radial measuring point arrangement method and measuring rake for flow tube of high-altitude platform | |
| CN105203327A (en) | Gas channel measurement parameter selecting method applied to engine gas channel analysis | |
| CN115356115B (en) | Layout method for mainstream flow field fine test in core machine environment | |
| CN115163330B (en) | Method for determining stability boundary of compression system of double-bypass core machine | |
| CN115575074A (en) | High-speed wind tunnel ventilation model internal resistance measurement uncertainty analysis method | |
| CN113250799B (en) | Backpressure data detection method, device and system | |
| CN110309534A (en) | A kind of diesel exhaust aftertreatment system structure design method | |
| CN215726268U (en) | Flow sensor verification system | |
| CN111721399B (en) | Hydraulic building structure vibration test system and test method | |
| CN116222487A (en) | Pre-air inlet flow pipe area measurement method and system | |
| CN111079321A (en) | Exhaust system silencer radiation noise calculation method | |
| CN105675245B (en) | High-precision Kriging test method for predicting flow field distribution based on measured values | |
| CN117113887B (en) | Method and device for correcting additional resistance of air inlet channel of indoor test bed of aero-engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |