CN112485014A - Split type turbofan engine nacelle force measurement test device with dynamic simulation and force measurement test method - Google Patents
Split type turbofan engine nacelle force measurement test device with dynamic simulation and force measurement test method Download PDFInfo
- Publication number
- CN112485014A CN112485014A CN202011281006.2A CN202011281006A CN112485014A CN 112485014 A CN112485014 A CN 112485014A CN 202011281006 A CN202011281006 A CN 202011281006A CN 112485014 A CN112485014 A CN 112485014A
- Authority
- CN
- China
- Prior art keywords
- nacelle
- pressure
- rod
- turbine
- rake
- 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
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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Fluid Mechanics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a split type force measuring test device and a force measuring test method for a turbofan engine nacelle with dynamic simulation, which comprises the following steps: a front end support mechanism; one end of the rod-type balance is connected with the front end supporting mechanism, the other end of the rod-type balance is connected with the nacelle, and a gap is formed between the nacelle and the front end supporting mechanism; a hub is arranged in the short cabin, and a fan blade disc is arranged on the hub; the supporting rod is internally provided with a transmission shaft, one end of the transmission shaft is fixedly connected with the propeller hub, the other end of the transmission shaft is provided with a turbine, the supporting rod is connected with a turbine casing, the turbine is positioned in the turbine casing, and the turbine casing is arranged on the rear end supporting mechanism; the pressure measuring rake is arranged on the supporting rod; the culvert guide vane is arranged at the end part of the strut. The invention can simulate the air flow of the inlet of the single nacelle by regulating the rotating speed of the fan, realize the accurate measurement of the model aerodynamic force under the influence of the air intake and exhaust of the simulation nacelle, and the obtained test data has important value for guiding the design and optimization of the whole turbofan engine nacelle and the airplane.
Description
Technical Field
The invention belongs to the field of power measurement of turbofan engines and turbofan engine nacelle models, and particularly relates to a split type force measurement test device and method for a turbofan engine nacelle with power simulation.
Background
The development of advanced civil aircraft increasingly emphasizes economy, safety, comfort and environmental protection, and puts higher and higher requirements on engines, pneumatic layout, materials and the like. In order to achieve excellent economy, civil aircraft generally adopt high bypass ratio turbofan engines to remarkably reduce the fuel consumption rate of the engines. The high bypass ratio engine mounting mode mainly has two kinds: hoisting under the wing or installing outside the body. The engine has large overall dimension and very rough appearance, and needs to be rectified by a nacelle with smooth appearance so as to reduce the flight resistance of the whole engine. Therefore, the aerodynamic design of the nacelle is of particular importance in order to obtain good flight performance of the aircraft.
The wind tunnel test is an important method for evaluating the appearance design of the nacelle. In the detailed pneumatic design stage of the civil aircraft, modes mainly comprising a cone plugging model test, a ventilation model test, an air inlet injection test, an exhaust jet flow model test, a power model test with a turbine and the like are distinguished for the simulation of the engine nacelle according to the simulation accuracy. The traditional cone blocking model can not simulate the influence of air intake and exhaust on the aerodynamic characteristics of the nacelle, at present, a ventilating nacelle test model with lower cost is generally adopted in the tests for researching the resistance characteristics, the divergence Mach number characteristics and the like of a single nacelle, and the method can simulate jet flow in a certain range but can not simulate air intake flow. The nacelle model test with turbine power can simulate important factors required to be considered by nacelle design, such as air inlet geometry, air outlet geometry, air inlet flow, exhaust flow, air inlet/exhaust interference and the like, and is an effective method for acquiring and improving the performance of the power nacelle.
The air intake flow coefficient obtained by the simple flow regulating device is about 0.4-0.7, which is lower than the flow coefficient of the nacelle under the flight condition by 0.6-2.0, and the influence of air intake and exhaust on the aerodynamic characteristics of the engine nacelle under the flight condition is difficult to accurately evaluate. Furthermore, conventional vent test nacelles are connected to a balance by a brace (as described in patent publication No. CN 207717325U), and the forces measured by the balance comprise the forces of the nacelle stand and are difficult to subtract. The invention makes the force measured by the balance only be the aerodynamic force of the nacelle through the ingenious design.
Disclosure of Invention
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages described hereinafter.
To achieve these objects and other advantages in accordance with the purpose of the invention, there is provided a split turbofan engine nacelle force measurement testing apparatus with dynamic simulation, comprising:
a front end support mechanism;
one end of the rod-type balance is connected with the front end supporting mechanism through a flange in a taper fit mode, the other end of the rod-type balance is connected with a nacelle, and a gap is formed between the nacelle and the front end supporting mechanism; a hub is arranged in the nacelle, and a fan blade disc is arranged on the hub;
the turbine structure comprises a support rod, a turbine casing and a rear end supporting mechanism, wherein a transmission shaft is arranged in the support rod, one end of the transmission shaft is fixedly connected with a propeller hub, the other end of the transmission shaft is provided with the turbine, the support rod is connected with the turbine casing, the turbine is positioned in the turbine casing, and the turbine casing is arranged on the rear end supporting mechanism;
the pressure measuring rake is arranged on the supporting rod and is positioned in the short cabin close to the outlet, and the pressure measuring rake is not in contact with the short cabin; and the outer culvert guide vane is arranged at the end part of the supporting rod and is positioned between the fan blade disc and the pressure measuring rake.
Preferably, wherein the structure of the front end support structure comprises:
the nacelle base is fixed on the wind tunnel wall plate through bolts, a nacelle support is arranged on the nacelle base, and one end of the rod balance is fixedly connected with the nacelle support through a flange in a taper fit mode; a gap is arranged between the nacelle and the nacelle bracket;
the structure of the rear end supporting mechanism comprises:
the turbine casing is fixedly arranged on the supporting joint;
and the supporting joint is fixedly connected to the wind tunnel semi-curved knife mechanism through a pin.
Preferably, the strut is provided with an outer culvert fairing with a smooth appearance through a screw, and the outer culvert fairing wraps the connecting part of the pressure measuring rake and the strut.
Preferably, a wedge-shaped angle changing sheet is arranged below the nacelle base.
Preferably, the nacelle bracket is symmetrical in cross section and has a symmetrical wing shape.
Preferably, the diameter of the fan blade disc is larger than 250mm, and the drop pressure ratio of the fan blade disc is 1.0-1.7.
A split type turbofan engine nacelle force measurement test device with dynamic simulation comprises the following force measurement test methods: the whole force measuring test device is arranged in a wind tunnelThe high-pressure gas in the wind tunnel drives the turbine to rotate, and then the turbine drives the transmission shaft and the fan blade disc to rotate so as to obtain the aerodynamic characteristics of the nacelle under the condition of simulating the influence of air intake and exhaust in a flight state; measuring total pressure, total temperature and static pressure in the nacelle through a pressure measuring rake, and measuring a load vector to the nacelle and a force vector generated by the self weight of the nacelle in a rod type balance shaft system through a rod type balance; during the test, the total pressure P of the incoming flow is changed0∞Mach number M∞Acquiring rod balance signals and signals of a pressure measuring rake under the conditions of fan blade disc and turbine rotating speed n, nacelle attack angle alpha and the like, and obtaining aerodynamic force test data of the nacelle through data processing; the data processing method comprises the following steps:
step one, calculating the actual flow m of the flow pipe where each total pressure measurement point on the pressure measurement rake is locatedeThe calculation method comprises the following steps:
wherein, P0eTotal pressure measured by pressure-measuring rake, AeFor the flow area, T, of the flow tube in which the single pressure-measuring point of the pressure-measuring rake is located0eTotal temperature, q (M), measured for the pressure rakee) Is the nacelle outlet section velocity pressure, q (M)e) The calculation method comprises the following steps:
wherein gamma is the specific heat ratio of incoming flow, the air dielectric constant is 1.4, and the outlet Mach number MeTotal pressure P measured by pressure measuring rake0eAnd static pressure PeConversion is carried out to obtain:
step two, calculating the ideal flow m of the flow pipe where each total pressure measuring point on the pressure measuring rake is locatedinThe calculation method comprises the following steps:
wherein A isinFor air intake capture area, T0For the total temperature of incoming flow, the pressure q (M) of incoming flow velocity∞) The calculation method comprises the following steps:
wherein, the incoming flow Mach number M∞Given test conditions;
step three, calculating the air inflow coefficient phi of the nacelle, wherein phi is sigma meAnd minThe ratio of (A) to (B):
φ＝∑me/min
step four, calculating the total aerodynamic force vector F of the nacellenacelleThe calculation method comprises the following steps:
Fnacelle＝E·(Fbl-FG)
wherein, FblLoad vector measured for bar balance, FGThe force vector is generated by the self weight of the nacelle in a rod type balance shaft system, and E is a transposed matrix from the rod type balance shaft system to a body shaft system;
calculating the flow resistance F in the nacelleinThe method is obtained by the momentum theorem and comprises the following steps:
due to the frictional resistance X of the outer duct of the nacelle modelinReflecting not the real engine nacelle internal flow characteristics and therefore should be subtracted, the aerodynamic and torque vectors F of the nacelle cowl are calculated as:
F＝Fnacelle-Fin
and obtaining the aerodynamic force test data of the nacelle by the airflow coefficient phi of the inlet air of the nacelle and the aerodynamic force F of the nacelle cover obtained in the first step to the fourth step.
The invention at least comprises the following beneficial effects: the invention can simulate the air flow of the inlet of the single nacelle by regulating the rotating speed of the fan, realize the accurate measurement of the model aerodynamic force under the influence of the air intake and exhaust of the simulation nacelle, and the obtained test data has important value for guiding the design and optimization of the whole turbofan engine nacelle and the airplane. According to the split turbofan engine nacelle force measurement test device with the power simulation, the rod balance is directly connected with the nacelle, so that the force measured by the rod balance is only the aerodynamic force of the nacelle.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Description of the drawings:
FIG. 1 is a schematic structural view of a split turbofan engine nacelle force measurement test device with power simulation provided by the invention;
FIG. 2 is a schematic view of the installation structure of the split turbofan engine nacelle force measurement test device with dynamic simulation provided by the invention.
The specific implementation mode is as follows:
the present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the invention by referring to the description text.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
It is to be understood that in the description of the present invention, the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are used only for convenience in describing the present invention and for simplification of the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, unless otherwise specifically stated or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are used broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection via an intermediate medium, or a communication between two elements, and those skilled in the art will understand the specific meaning of the terms in the present invention specifically.
Further, in the present invention, unless otherwise explicitly specified or limited, a first feature "on" or "under" a second feature may be directly contacted with the first and second features, or indirectly contacted with the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
As shown in fig. 1-2: the invention relates to a split type turbofan engine nacelle force measurement test device with dynamic simulation, which comprises:
a front end support mechanism;
one end of the rod-type balance 12 is connected with the front end supporting mechanism through a flange in a taper fit mode, the other end of the rod-type balance is connected with the nacelle 1, and a gap is formed between the nacelle 1 and the front end supporting mechanism; a hub 11 is arranged in the nacelle 1, and a fan blade disc 2 is arranged on the hub 11;
the turbine structure comprises a support rod 6, a transmission shaft 7 is arranged in the support rod, one end of the transmission shaft 7 is fixedly connected with a propeller hub 11, a turbine 9 is arranged at the other end of the transmission shaft, the support rod 6 is connected with a turbine casing 8, the turbine 9 is positioned in the turbine casing 8, and the turbine casing 8 is arranged on a rear end supporting mechanism;
the pressure measuring rake 4 is arranged on the supporting rod 6 and is positioned in the nacelle 1 close to the outlet, and the pressure measuring rake 4 is not in contact with the nacelle 1; and the outer culvert guide vane 3 is arranged at the end part of the supporting rod 6, and the outer culvert guide vane 3 is positioned between the fan blade disc 2 and the pressure measuring rake 4.
Force measurement principle: the whole force measuring test device is placed in a wind tunnel, a turbine 9 is driven to rotate through high-pressure gas in the wind tunnel, and then a transmission shaft 7 and a fan blade disc 2 are driven to rotate through the turbine 9 and used for obtaining aerodynamic characteristics of the nacelle under the condition of simulating air intake and exhaust influences in a flight state; measuring total pressure and static pressure in the nacelle through the pressure measuring rake 4, and measuring a load vector to the nacelle 1 and a force vector generated by the self weight of the nacelle 1 in a shaft system of the rod balance 12 through the rod balance 12; during the test, the total pressure P of the incoming flow is changed0∞Mach number m∞The rotating speed n of the fan blade disc 2 and the turbine 9, the attack angle alpha of the nacelle 1 and the like, and acquiring signals of the rod balance 12 and pressure signals of the pressure measuring rake 4, and acquiring aerodynamic force test data of the nacelle 1 through data processing. The front end supporting mechanism and the rear end supporting mechanism are used for supporting the whole force measuring test device. The bypass guide vanes 3 are used for guiding airflow and adjusting the flow velocity of the air. The force measuring device provided by the invention adopts a split structure, namely, the nacelle 1 is not directly connected with the front end supporting mechanism, and a gap is reserved between the lower surface of the nacelle 1 and the upper end surface of the front end supporting mechanism, so that the force measured by the rod balance 12 is only aerodynamic force on the inner surface and the outer surface of the nacelle 1, and the problem that the measured force of the front end supporting mechanism is difficult to deduct is solved.
In the above technical solution, the structure of the front end support structure includes:
the nacelle base 14 is fixed on a wind tunnel wall plate 15 through bolts, a nacelle support 13 is arranged on the nacelle base 14, and one end of the rod balance 12 is fixedly connected with the nacelle support 13 through a flange in a taper fit mode; a gap is arranged between the nacelle 1 and the nacelle support 13, so that the force measured by the rod balance 12 is only the aerodynamic force of the nacelle 2;
the structure of the rear end supporting mechanism comprises:
the support joint 10 is fixedly arranged on the turbine casing 8;
the wind tunnel semi-curved knife mechanism 16 is characterized in that the supporting joint 10 is fixedly connected to the wind tunnel semi-curved knife mechanism 16 through a pin. The wind tunnel semi-curved knife mechanism 16 is used as a wind tunnel attack angle mechanism, and the supporting joint 10 can adjust the geometric shape and the size according to the concrete interface conditions of the wind tunnel semi-curved knife mechanism 16
In the technical scheme, the supporting rod 6 is provided with the culvert fairing 5 with a smooth appearance through a screw, the culvert fairing 5 wraps the connecting part of the pressure measuring rake 4 and the supporting rod 6, and the culvert fairing 5 with the smooth appearance has the functions of exhausting and rectifying at the exhaust port of the nacelle 1.
In the above technical solution, a wedge-shaped angle transformer 17 is arranged below the nacelle base 14, and the test attack angle of the nacelle 1 can be changed by replacing different wedge-shaped angle transformers 17.
In the above technical solution, the nacelle bracket 13 has a symmetrical wing-shaped cross section, and this arrangement can reduce the disturbance of aerodynamic force of the nacelle bracket 13 on the nacelle 1.
In the technical scheme, the diameter of the fan blade disc is larger than 250mm, the drop pressure ratio of the fan blade disc is 1.0-1.7, and the split type turbofan engine nacelle force measurement test device with power simulation, provided by the invention, is suitable for wind tunnels above 2 meter level
A split type turbofan engine nacelle force measurement test device with dynamic simulation comprises the following force measurement test methods: the whole force measurement test device is placed in a wind tunnel, a turbine is driven to rotate through high-pressure gas in the wind tunnel, and then a transmission shaft and a fan blade disc are driven to rotate through the turbine so as to obtain the aerodynamic characteristics of the nacelle under the condition of simulating the influence of air intake and exhaust in a flight state; measuring total pressure, total temperature and static pressure in the nacelle through a pressure measuring rake, and measuring a load vector to the nacelle and a force vector generated by the self weight of the nacelle in a rod type balance shaft system through a rod type balance; during the test, the total pressure P of the incoming flow is changed0∞Mach number M∞Acquiring rod balance signals and signals of a pressure measuring rake under the conditions of fan blade disc and turbine rotating speed n, nacelle attack angle alpha and the like, and obtaining aerodynamic force test data of the nacelle through data processing; the data processing method comprises the following steps:
step one, calculating the actual flow m of the flow pipe where each total pressure measurement point on the pressure measurement rake is locatedeThe calculation method is：
Wherein, P0eTotal pressure measured by pressure-measuring rake, AeFor the flow area, T, of the flow tube in which the single pressure-measuring point of the pressure-measuring rake is located0eTotal temperature, q (M), measured for the pressure rakee) Is the nacelle outlet section velocity pressure, q (M)e) The calculation method comprises the following steps:
wherein gamma is the specific heat ratio of incoming flow, the air dielectric constant is 1.4, and the outlet Mach number MeTotal pressure P measured by pressure measuring rake0eAnd static pressure PeConversion is carried out to obtain:
step two, calculating the ideal flow m of the flow pipe where each total pressure measuring point on the pressure measuring rake is locatedinThe calculation method comprises the following steps:
wherein A isinFor air intake capture area, T0For the total temperature of incoming flow, the pressure q (M) of incoming flow velocity∞) The calculation method comprises the following steps:
wherein, the incoming flow Mach number M∞Given test conditions;
step three, calculating the air inflow coefficient phi of the nacelle, wherein phi is sigma meAnd minThe ratio of (A) to (B):
φ＝∑me/min
step four, calculating the total aerodynamic force vector F of the nacellenacelleThe calculation method comprises the following steps:
Fnacelle＝E·(Fbl-FG)
wherein, FblLoad vector measured for bar balance, FGThe force vector is generated by the self weight of the nacelle in a rod type balance shaft system, and E is a transposed matrix from the rod type balance shaft system to a body shaft system;
calculating the flow resistance F in the nacelleinThe method is obtained by the momentum theorem and comprises the following steps:
due to the frictional resistance X of the outer duct of the nacelle modelinReflecting not the real engine nacelle internal flow characteristics and therefore should be subtracted, the aerodynamic and torque vectors F of the nacelle cowl are calculated as:
F＝Fnacelle-Fin
and obtaining the aerodynamic force test data of the nacelle by the airflow coefficient phi of the inlet air of the nacelle and the aerodynamic force F of the nacelle cover obtained in the first step to the fourth step.
The number of apparatuses and the scale of the process described herein are intended to simplify the description of the present invention. Applications, modifications and variations of the present invention will be apparent to those skilled in the art.
While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable in various fields of endeavor to which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.
Claims (7)
1. The utility model provides a split type turbofan engine nacelle dynamometry test device of taking power simulation which characterized in that includes:
a front end support mechanism;
one end of the rod-type balance is connected with the front end supporting mechanism through a flange in a taper fit mode, the other end of the rod-type balance is connected with a nacelle, and a gap is formed between the nacelle and the front end supporting mechanism; a hub is arranged in the nacelle, and a fan blade disc is arranged on the hub;
the turbine structure comprises a support rod, a turbine casing and a rear end supporting mechanism, wherein a transmission shaft is arranged in the support rod, one end of the transmission shaft is fixedly connected with a propeller hub, the other end of the transmission shaft is provided with the turbine, the support rod is connected with the turbine casing, the turbine is positioned in the turbine casing, and the turbine casing is arranged on the rear end supporting mechanism;
the pressure measuring rake is arranged on the supporting rod and is positioned in the short cabin close to the outlet, and the pressure measuring rake is not in contact with the short cabin; and the outer culvert guide vane is arranged at the end part of the supporting rod and is positioned between the fan blade disc and the pressure measuring rake.
2. The split turbofan engine nacelle force measurement testing apparatus with dynamic simulation of claim 1 wherein the structure of the front end support structure comprises:
the nacelle base is fixed on the wind tunnel wall plate through bolts, a nacelle support is arranged on the nacelle base, and one end of the rod balance is fixedly connected with the nacelle support through a flange in a taper fit mode; a gap is arranged between the nacelle and the nacelle bracket;
the structure of the rear end supporting mechanism comprises:
the turbine casing is fixedly arranged on the supporting joint;
and the supporting joint is fixedly connected to the wind tunnel semi-curved knife mechanism through a pin.
3. The split turbofan engine nacelle force measurement test device with dynamic simulation of claim 1, wherein the strut is provided with a culvert fairing with a smooth shape by screws, and the culvert fairing covers the connection part of the pressure measurement rake and the strut.
4. The split turbofan engine nacelle force measurement testing apparatus with dynamic simulation of claim 2 wherein a wedge-shaped angle transformer is disposed below the nacelle base.
5. The split turbofan engine nacelle force measurement testing apparatus with dynamic simulation of claim 2 wherein the nacelle cradle cross section is a symmetrical airfoil.
6. The split turbofan engine nacelle force measurement test device with power simulation of claim 1 wherein the diameter of the fan blade disc is greater than 250mm and the drop pressure ratio of the fan blade disc is 1.0-1.7.
7. The split turbofan engine nacelle force measurement test device with power simulation of any one of claims 1 to 6, wherein the force measurement test method is as follows: the whole force measurement test device is placed in a wind tunnel, a turbine is driven to rotate through high-pressure gas in the wind tunnel, and then a transmission shaft and a fan blade disc are driven to rotate through the turbine so as to obtain the aerodynamic characteristics of the nacelle under the condition of simulating the influence of air intake and exhaust in a flight state; measuring total pressure, total temperature and static pressure in the nacelle through a pressure measuring rake, and measuring a load vector to the nacelle and a force vector generated by the self weight of the nacelle in a rod type balance shaft system through a rod type balance; during the test, the total pressure P of the incoming flow is changed0∞Mach number M∞Acquiring rod balance signals and signals of a pressure measuring rake under the conditions of fan blade disc and turbine rotating speed n, nacelle attack angle alpha and the like, and obtaining aerodynamic force test data of the nacelle through data processing; the data processing method comprises the following steps:
step one, calculating the actual flow m of the flow pipe where each total pressure measurement point on the pressure measurement rake is locatedeThe calculation method comprises the following steps:
wherein, P0eTotal pressure measured by pressure-measuring rake, AeFor the flow area, T, of the flow tube in which the single pressure-measuring point of the pressure-measuring rake is located0eTotal temperature, q (M), measured for the pressure rakee) Is the nacelle outlet section velocity pressure, q (M)e) The calculation method comprises the following steps:
wherein gamma is the specific heat ratio of incoming flow, the air dielectric constant is 1.4, and the outlet Mach number MeTotal pressure P measured by pressure measuring rake0eAnd static pressure PeConversion is carried out to obtain:
step two, calculating the ideal flow m of the flow pipe where each total pressure measuring point on the pressure measuring rake is locatedinThe calculation method comprises the following steps:
wherein A isinFor air intake capture area, T0For the total temperature of incoming flow, the pressure q (M) of incoming flow velocity∞) The calculation method comprises the following steps:
wherein, the incoming flow Mach number M∞Given test conditions;
step three, calculating the air inflow coefficient phi of the nacelle, wherein phi is sigma meAnd minThe ratio of (A) to (B):
φ＝∑me/min
step four, calculating the total aerodynamic force vector F of the nacellenacelleMethod of calculationComprises the following steps:
Fnacelle＝E·(Fbl-FG)
wherein, FblLoad vector measured for bar balance, FGThe force vector is generated by the self weight of the nacelle in a rod type balance shaft system, and E is a transposed matrix from the rod type balance shaft system to a body shaft system;
calculating the flow resistance F in the nacelleinThe method is obtained by the momentum theorem and comprises the following steps:
due to the frictional resistance X of the outer duct of the nacelle modelinReflecting not the real engine nacelle internal flow characteristics and therefore should be subtracted, the aerodynamic and torque vectors F of the nacelle cowl are calculated as:
F＝Fnacelle-Fin
and obtaining the aerodynamic force test data of the nacelle by the airflow coefficient phi of the inlet air of the nacelle and the aerodynamic force F of the nacelle cover obtained in the first step to the fourth step.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011281006.2A CN112485014B (en) | 2020-11-16 | 2020-11-16 | Split type turbofan engine nacelle force measurement test device with dynamic simulation and force measurement test method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011281006.2A CN112485014B (en) | 2020-11-16 | 2020-11-16 | Split type turbofan engine nacelle force measurement test device with dynamic simulation and force measurement test method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112485014A true CN112485014A (en) | 2021-03-12 |
| CN112485014B CN112485014B (en) | 2021-08-03 |
Family
ID=74930803
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011281006.2A Active CN112485014B (en) | 2020-11-16 | 2020-11-16 | Split type turbofan engine nacelle force measurement test device with dynamic simulation and force measurement test method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112485014B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113029502A (en) * | 2021-04-20 | 2021-06-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle wind tunnel test method for simultaneously simulating air intake and air exhaust |
| CN113092118A (en) * | 2021-06-09 | 2021-07-09 | 中国航发上海商用航空发动机制造有限责任公司 | Full-scale fan-booster stage performance test device and test method |
| CN113252280A (en) * | 2021-04-20 | 2021-08-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle test device capable of simulating air intake and exhaust simultaneously |
| CN113267313A (en) * | 2021-07-19 | 2021-08-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Pressure measuring rake and stabilizing method thereof |
| CN114061887A (en) * | 2021-12-01 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Amphibious aircraft power lift-increasing full-mode wind tunnel test device |
| CN114136643A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Aeroengine air flow measuring point layout method |
| CN114486276A (en) * | 2021-12-29 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Turboprop aircraft outer lubricating oil system and engine ground rack joint test device |
| CN118067351A (en) * | 2024-04-17 | 2024-05-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test method for resistance characteristics of nacelle of civil aircraft engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101676918A (en) * | 2008-09-18 | 2010-03-24 | 中国航空工业第一集团公司沈阳发动机设计研究所 | Pneumatic design method for separation type exhaust jet pipe of high bypass ratio engine |
| US20160011068A1 (en) * | 2013-03-08 | 2016-01-14 | U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration | In-Situ Load System for Calibrating and Validating Aerodynamic Properties of Scaled Aircraft in Ground-Based Aerospace Testing Applications |
| CN105574220A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Calculation method of internal resistance of engine nacelle |
| CN107462291A (en) * | 2017-08-02 | 2017-12-12 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of high-precision high voltage gas flow measurement and control device |
| CN107860552A (en) * | 2017-12-26 | 2018-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of measurement apparatus of fanjet nacelle spillage drag |
| US10450955B2 (en) * | 2016-07-06 | 2019-10-22 | United Technologies Corporation | Nacelle anti ice system |
| CN110487507A (en) * | 2019-09-06 | 2019-11-22 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of five component strain balances for nacelle internal resistance dynamometer check |
| US10684183B2 (en) * | 2018-04-24 | 2020-06-16 | The Boeing Company | Powered total pressure measurement rake with telemetry |
-
2020
- 2020-11-16 CN CN202011281006.2A patent/CN112485014B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101676918A (en) * | 2008-09-18 | 2010-03-24 | 中国航空工业第一集团公司沈阳发动机设计研究所 | Pneumatic design method for separation type exhaust jet pipe of high bypass ratio engine |
| US20160011068A1 (en) * | 2013-03-08 | 2016-01-14 | U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration | In-Situ Load System for Calibrating and Validating Aerodynamic Properties of Scaled Aircraft in Ground-Based Aerospace Testing Applications |
| CN105574220A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Calculation method of internal resistance of engine nacelle |
| US10450955B2 (en) * | 2016-07-06 | 2019-10-22 | United Technologies Corporation | Nacelle anti ice system |
| CN107462291A (en) * | 2017-08-02 | 2017-12-12 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of high-precision high voltage gas flow measurement and control device |
| CN107860552A (en) * | 2017-12-26 | 2018-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of measurement apparatus of fanjet nacelle spillage drag |
| US10684183B2 (en) * | 2018-04-24 | 2020-06-16 | The Boeing Company | Powered total pressure measurement rake with telemetry |
| CN110487507A (en) * | 2019-09-06 | 2019-11-22 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of five component strain balances for nacelle internal resistance dynamometer check |
Non-Patent Citations (2)
| Title |
|---|
| 曲方亮 等: "高速风洞引射式进排气动力模拟试验研究", 《流体力学实验与测量》 * |
| 章欣涛 等: "民用航空涡扇发动机短舱外部阻力试验方法研究", 《推进技术》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113252280A (en) * | 2021-04-20 | 2021-08-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle test device capable of simulating air intake and exhaust simultaneously |
| CN113029502A (en) * | 2021-04-20 | 2021-06-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle wind tunnel test method for simultaneously simulating air intake and air exhaust |
| CN113029502B (en) * | 2021-04-20 | 2023-03-31 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle wind tunnel test method for simultaneously simulating air intake and air exhaust |
| CN113252280B (en) * | 2021-04-20 | 2021-09-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Nacelle test device capable of simulating air intake and exhaust simultaneously |
| CN113092118B (en) * | 2021-06-09 | 2021-09-28 | 中国航发上海商用航空发动机制造有限责任公司 | Full-scale fan-booster stage performance test device and test method |
| CN113092118A (en) * | 2021-06-09 | 2021-07-09 | 中国航发上海商用航空发动机制造有限责任公司 | Full-scale fan-booster stage performance test device and test method |
| CN113267313A (en) * | 2021-07-19 | 2021-08-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Pressure measuring rake and stabilizing method thereof |
| CN113267313B (en) * | 2021-07-19 | 2021-09-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Pressure measuring rake and stabilizing method thereof |
| CN114136643A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Aeroengine air flow measuring point layout method |
| CN114136643B (en) * | 2021-10-20 | 2024-01-09 | 中国航发四川燃气涡轮研究院 | Aeroengine air flow measuring point layout method |
| CN114061887A (en) * | 2021-12-01 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Amphibious aircraft power lift-increasing full-mode wind tunnel test device |
| CN114061887B (en) * | 2021-12-01 | 2023-04-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Amphibious aircraft power rise-increasing full-mode wind tunnel test device |
| CN114486276A (en) * | 2021-12-29 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Turboprop aircraft outer lubricating oil system and engine ground rack joint test device |
| CN118067351A (en) * | 2024-04-17 | 2024-05-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test method for resistance characteristics of nacelle of civil aircraft engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112485014B (en) | 2021-08-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112485014B (en) | Split type turbofan engine nacelle force measurement test device with dynamic simulation and force measurement test method | |
| CN112485013B (en) | Single turbofan engine nacelle surface pressure measurement test device with turbine power simulation and pressure measurement test method | |
| Chen et al. | Blockage corrections in wind tunnel tests of small horizontal-axis wind turbines | |
| Reid | Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ration of 1.82 | |
| CN113029502B (en) | Nacelle wind tunnel test method for simultaneously simulating air intake and air exhaust | |
| Hall et al. | Measurements of intake separation hysteresis in a model fan and nacelle rig | |
| CN116399547B (en) | Aircraft ventilation force measurement wind tunnel test device, installation method and test method thereof | |
| Johnston et al. | Unsteady wing surface pressures in the wake of a propeller | |
| CN110926824B (en) | Device and method for measuring internal circulation wind resistance characteristic and heat dissipation capacity of generator | |
| CN116448374A (en) | Air inlet duct wind tunnel test method for simulating multiple interference | |
| Zhang et al. | Rotor performance of an axial flow compressor at free and highly loaded windmilling conditions | |
| CN113252280B (en) | Nacelle test device capable of simulating air intake and exhaust simultaneously | |
| Zell et al. | Performance and test section flow characteristics of the national full-scale aerodynamics complex 40-by 80-foot wind tunnel | |
| CN118067351B (en) | Wind tunnel test method for resistance characteristics of nacelle of civil aircraft engine | |
| Patterson Jr | A wind tunnel investigation of jet-wake effect of a high-bypass engine on wing-nacelle interference drag of a subsonic transport | |
| Tsukamoto et al. | Measurement and numerical simulation of a small centrifugal compressor characteristics at small or negative flow rate | |
| Osborn et al. | Effect of simulated downstream flow blockage doors on the performance of an axial-flow fan rotor | |
| Cherry et al. | The aerodynamic design and performance of the NASA/GE e3 low pressure turbine | |
| CN116399548B (en) | Air inlet channel inner surface aerodynamic characteristic measurement test device and installation and test method thereof | |
| CN115855514B (en) | Double-bending special-shaped variable cross-section air inlet test device for vortex paddle power high-altitude bench test | |
| Robbins et al. | Investigation of an Axial-flow-compressor Rotor with Circular-arc Blades Operating up to a Rotor-inlet Relative Mach Number of 1.22 | |
| RU2681548C1 (en) | Method of stand tests of turbo-reactive two-circuit motor | |
| HUGHES et al. | Low-speed wind tunnel performance of high-speed counterrotation propellers at angle-of-attack | |
| Balan | Design considerations of a versatile simulator for high-bypass turbofans | |
| Wesoky et al. | Low-speed wind tunnel tests of a 50.8-centimeter (20-in.) 1.15-pressure-ratio fan engine model |
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 |