CN115585153A - Method for determining pressure distortion sensitive coefficient of compression system - Google Patents
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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Abstract
The invention provides a method for determining a pressure distortion sensitive coefficient of a compression system, wherein the compression system comprises a core machine driving fan and an air compressor, and the method comprises the following steps: s1: designing a distortion generating device; s2: placing a core machine driving fan and a gas compressor in a compression system, and respectively obtaining pneumatic performance parameters; s3: and calculating the sensitivity coefficient according to the pneumatic performance parameters obtained in the step S2. The method considers the sequence of the instability of the CDFS and the compressor, can accurately simulate the distortion condition of a real flow field at the inlet of the compressor, obtains the pressure distortion sensitive coefficients of the compression system and the sub-components in the working environment matched with the CDFS and the compressor, solves the problem that the pressure distortion sensitive coefficients of the compression system and the sub-components in the working environment cannot be accurately obtained, and can be widely applied to the intake pressure distortion test of the engine/compression components.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a method for determining a pressure distortion sensitive coefficient of a compression system.
Background
The compressor is one of the key components of the gas turbine engine, the aerodynamic stability of the compressor is the main factor determining the stability of the gas turbine engine, and the strong pressurization process of the airflow inside the compressor determines the aerodynamic instability of the compressor. At present, a compressor structure with a core engine driving fan (CDFS) is commonly used in a variable cycle engine, and a schematic structural diagram of the compressor structure is shown in fig. 4, and an outer duct is arranged at an outlet of the CDFS for shunting. Considering the following of the variable-cycle engine to high stealth performance and the strong coupling aerodynamic influence of the CDFS and the compressor, the higher requirement is provided for the aerodynamic stability of the CDFS and the compressor. Therefore, how to accurately acquire the pressure distortion sensitivity coefficient of the compression system becomes crucial.
The intake pressure distortion test is one of the important channels for obtaining the pressure distortion sensitive coefficient at present, and the independent pressure distortion sensitive coefficient is obtained by adopting a method of carrying out the distortion test by a single compression component in the past. However, due to the strong coupling design of the CDFS and the compressor, the following problems still exist in the single test mode:
1) The instability sequence of the CDFS and the compressor cannot be identified;
2) The distortion condition of the real flow field of the inlet of the gas compressor cannot be accurately simulated;
3) The pressure distortion sensitive coefficients of a compression system and sub-components under the working environment that the CDFS and the compressor are matched cannot be obtained.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide a method for determining a pressure distortion sensitivity coefficient of a compression system, wherein the compression system is a compressor structure with a CDFS. The method considers the sequence of the instability of the CDFS and the compressor, can accurately simulate the distortion condition of the real flow field at the inlet of the compressor, and obtains the pressure distortion sensitive coefficients of a compression system and sub-components under the working environment that the CDFS and the compressor are matched.
In order to achieve the above object, the present invention provides the following technical solutions, and provides a method for determining a pressure distortion sensitivity coefficient of a compression system, where the compression system includes a core engine driving fan and a compressor, and the method includes the following steps:
s1: designing a distortion generating device;
s2: placing a core machine driving fan and a gas compressor in a compression system, and respectively obtaining the compression system, the core machine driving fan in the compression system and the pneumatic performance parameters of the gas compressor in the compression system;
s3: and calculating the sensitivity coefficients of the compression system, the core machine driving fan and the air compressor respectively through the pneumatic performance parameters obtained in the step S2.
The method for determining the pressure distortion sensitive coefficient of the compression system is further characterized in that the distortion generating device in the S1 is of a fan-shaped inserting plate structure.
The method for determining the pressure distortion sensitive coefficient of the compression system is further characterized in that the fan-shaped angle theta of the fan-shaped inserting plate structure is 150-180 degrees; the thickness of the fan-shaped inserting plate is 10-20mm; the insertion depth L of the fan-shaped inserting plate is 0.1D-0.5D, wherein D is the diameter of an air inlet channel of the compression system.
The method for determining the pressure distortion sensitivity coefficient of the compression system also has the characteristic that the plug board is arranged at the 2D-3D position upstream of the inlet of the core machine driving fan in the test process.
The method for determining the pressure distortion sensitivity coefficient of the compression system provided by the invention also has the characteristics that the pneumatic performance of the compression system is obtained by the following steps:
a) Keeping the original regulation rule unchanged, wherein the regulation rule comprises the CDFS inlet guide vane angle beta CF0 Inlet guide vane angle beta of gas compressor C0 And a bypass ratio B 0 ；
b) Carrying out a uniform flow test, and measuring the pneumatic performance parameters of the compression system;
c) After the distortion generating device is inserted into the air inlet channel, a distortion flow test is carried out, and the flow pressure ratio characteristic of the compression system and the comprehensive distortion index W of the inlet of the compression system are measured CF 。
The method for determining the pressure distortion sensitive coefficient of the compression system has the characteristics that each characteristic line is not less than 6 points when the pneumatic performance parameters of the compression system are measured in a uniform flow test, and a complete characteristic line can be formed.
The method for determining the pressure distortion sensitive coefficient of the compression system provided by the invention is also characterized in that the steps for acquiring the pneumatic performance of the core machine driving fan in the compression system are as follows:
a: keeping the original regulation rule unchanged, developing a uniform flow test, and measuring the flow pressure ratio characteristic of the core machine driving fan;
b: in the surge point parameter measuring process, if the gas compressor is unstable at first, the angle of the inlet guide vane of the gas compressor is reduced by 0.5 degrees, and meanwhile, the angle is reduced by 0.1B 0 The bypass ratio of (a);
c: repeating the step B) until the core engine driving fan is firstly instable, and recording the inlet guide vane angle beta of the gas compressor at the moment C1 And bypass ratio B 1 And measuring asthma point parameters;
d: if the guide vane angle and the duct ratio are still unstable firstly when the limiting boundary is reached, the pressure distortion sensitive coefficient of the core engine driving fan in the system is zero, and the distortion flow test is not carried out any more;
e: retention of beta CF0 、β C1 、B 1 The regulation rule of the core machine driving fan is not changed, a distortion flow test is carried out, and the flow pressure ratio characteristic of the core machine driving fan and the comprehensive distortion index of the inlet of the core machine driving fan are measured
The method for determining the pressure distortion sensitivity coefficient of the compression system provided by the invention also has the characteristics that the pneumatic performance of the compressor in the compression system is obtained by the following steps:
a) Keeping the original regulation rule unchanged, carrying out a uniform flow test, and measuring the flow pressure ratio characteristic of the gas compressor;
b) In the surge point parameter measuring process, if the core machine driving fan is unstable at first, the angle of the inlet guide vane of the core machine driving fan is reduced by 0.5 degrees, and the same is true for the core machine driving fanIncrease in time by 0.1B 0 A bypass ratio of (c);
c) Repeating the step b) until the compressor is firstly unstable, and recording the inlet guide vane angle beta of the core machine driving fan at the moment CF1 And bypass ratio B 2 And measuring asthma point parameters;
d) If the fan is still driven by the core machine to be unstable when the guide vane angle and the bypass ratio reach the limit boundary, the pressure distortion sensitive coefficient of the compressor in the system is zero, and the distortion flow test is not carried out any more;
e) Maintenance of beta CF0 、β CF1 、B 2 The regulation rule of the pressure sensor is not changed, a distortion flow test is carried out, the flow pressure ratio characteristic of the air compressor and the comprehensive distortion index of the inlet of the air compressor are measured
The method for determining the pressure distortion sensitive coefficient of the compression system, provided by the invention, is further characterized in that the step of calculating the pressure distortion sensitive coefficient in the S3 is as follows:
s3.1: calculating the stability margin SM under uniform air intake conditions uni
SM uni ＝(π 1 /W c1 )/(π 2 /W c2 ) -1
Wherein, pi 1 Surge ratio, W, for uniform flow characteristics c1 Converting the flow rate for the surge point of the uniform flow characteristic; pi 2 For uniform flow operating point pressure ratio, W c2 Converting the flow rate for the uniform flow operating point;
s3.2: calculating the stability margin SM under distorted air intake conditions uni
SM dis ＝(π 3 /W c3 )/(π 4 /W c4 ) -1
Wherein, pi 3 The asthma-point pressure ratio, W, being of the distorted flow characteristics c3 Conversion of flow rate of surge point for distorted flow characteristics, pi 4 Is the distortion flow operating point pressure ratio, W c4 Converting the flow for the distortion flow working point;
s3.3: calculating the pressure distortion sensitivity coefficient alpha
Wherein,
is the inlet integrated distortion index.
Advantageous effects
The method for determining the pressure distortion sensitive coefficient of the compression system considers the sequence of the instability of the CDFS and the compressor, can accurately simulate the distortion condition of a real flow field at the inlet of the compressor, obtains the pressure distortion sensitive coefficient of the compression system and the sub-component under the working environment matched with the CDFS and the compressor, solves the problem that the pressure distortion sensitive coefficient of the compression system and the sub-component under the working environment cannot be accurately obtained, and can be widely applied to the intake pressure distortion test of an engine/compression component.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings required to be used in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a flow chart of a method for determining a pressure distortion sensitivity coefficient of a compression system according to an embodiment of the present invention;
FIG. 2 is a schematic view of a sector-shaped fixed board according to an embodiment of the present invention;
FIG. 3 is a diagram illustrating characteristics and operating lines of a method for determining a pressure distortion sensitivity coefficient of a compression system according to an embodiment of the present invention;
fig. 4 is a schematic view of a compressor with a CDFS.
Detailed Description
The present invention is further described in detail with reference to the drawings and examples, but it should be understood that these embodiments are not intended to limit the present invention, and those skilled in the art should understand that the functional, methodological, or structural equivalents of these embodiments or substitutions may be included in the scope of the present invention.
In the description of the embodiments of the present invention, it should be understood that the terms "central," "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are only for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As shown in fig. 1 to 3, an embodiment of the present invention provides a method for determining a pressure distortion sensitivity coefficient of a compression system, where the compression system includes a core engine driving fan and a compressor, and the method includes the following steps:
s1: designing a distortion generating device;
s2: placing a core machine driving fan and a gas compressor in a compression system, and respectively obtaining the compression system, the core machine driving fan in the compression system and the pneumatic performance parameters of the gas compressor in the compression system;
s3: and calculating the sensitivity coefficients of the compression system, the core machine driving fan and the air compressor respectively through the pneumatic performance parameters obtained in the step S2.
In some embodiments, the distortion generating device in S1 is a fan-shaped board structure.
In some embodiments, the fan-shaped inserting plate structure has a fan-shaped angle theta of 150-180 degrees; the thickness of the fan-shaped inserting plate is 10-20mm; the insertion depth L of the fan-shaped inserting plate is 0.1D-0.5D, wherein D is the diameter of an air inlet channel of the compression system. In order to meet the requirements of different intake distortion strengths in the test, the insertion depth takes 0.1D as an interval threshold value to carry out a plurality of values.
In some embodiments, the insert plate is installed 2D-3D upstream of the core engine driven fan inlet during the test.
In some embodiments, the pneumatic performance of the compression system is obtained by the following steps:
a) Keeping the original regulation rule unchanged, wherein the regulation rule comprises the angle beta of the CDFS inlet guide vane CF0 Inlet guide vane angle beta of gas compressor C0 And bypass ratio B 0 ；
b) Carrying out a uniform flow test, and measuring the pneumatic performance parameters of the compression system;
c) After the distortion generating device is inserted into the air inlet channel, a distortion flow test is carried out, and the flow pressure ratio characteristic of the compression system and the comprehensive distortion index of the inlet of the compression system are measured
In some embodiments, in the homogeneous flow test, each characteristic line is no less than 6 points when measuring aerodynamic performance parameters of the compression system, and it is ensured that a complete characteristic line can be formed.
In some embodiments, the step of obtaining the aerodynamic performance of the core engine driven fan in the compression system comprises:
a: keeping the original regulation rule unchanged, developing a uniform flow test, and measuring the flow pressure ratio characteristic of the core machine driving fan;
b: in the surge point parameter measuring process, if the gas compressor is unstable at first, the angle of the inlet guide vane of the gas compressor is reduced by 0.5 degrees, and meanwhile, the angle is reduced by 0.1B 0 The bypass ratio of (a);
c: repeating the step B) until the core engine driving fan is firstly instable, and recording the inlet guide vane angle beta of the gas compressor at the moment C1 And bypass ratio B 1 And measuring asthma point parameters;
d: if the guide vane angle and the duct ratio still cause the compressor to be unstable firstly when reaching the limit boundary, the pressure distortion sensitive coefficient of the core engine driving fan in the system is zero, and the distortion flow test is not carried out any more;
e: retention of beta CF0 、β C1 、B 1 The regulation rule is unchanged, a distortion flow test is carried out, and the flow pressure ratio characteristic of the core machine driving fan and the comprehensive distortion index of the inlet of the core machine driving fan are measured
In some embodiments, the pneumatic performance of the compressor in the compression system is obtained by the following steps:
a) Keeping the original regulation rule unchanged, carrying out a uniform flow test, and measuring the flow pressure ratio characteristic of the gas compressor;
b) In the surge point parameter measuring process, if the core machine driving fan is unstable at first, the angle of the inlet guide vane of the core machine driving fan is reduced by 0.5 degrees, and the angle of the inlet guide vane of the core machine driving fan is increased by 0.1B 0 The bypass ratio of (a);
c) Repeating the step b) until the compressor is firstly unstable, and recording the inlet guide vane angle beta of the core machine driving fan at the moment CF1 And bypass ratio B 2 And measuring asthma point parameters;
d) If the fan is still driven by the core engine to be unstable when the guide vane angle and the duct ratio reach the limit boundary, the pressure distortion sensitive coefficient of the compressor in the system is zero, and the distortion flow test is not carried out any more;
e) Retention of beta CF0 、β CF1 、B 2 The regulation rule of the pressure sensor is not changed, a distortion flow test is carried out, and the flow pressure ratio characteristic of the gas compressor and the comprehensive distortion index of the inlet of the gas compressor are measured
In the distortion flow test in the above embodiment, when the surge point parameter is measured, in order to respectively obtain the surge point flow and the pressure ratio of the CDFS and the compressor, and the corresponding inlet comprehensive distortion index, the CDFS and the compressor need to be respectively made into first-generation instability components. Therefore, the matching between the CDFS and the compressor needs to be changed by specific measures, and the measures comprise changing the angle of the CDFS inlet guide vane, the angle of the compressor inlet guide vane and the bypass ratio.
In some embodiments, the pressure distortion sensitivity coefficient is an important index for characterizing the intake pressure distortion resistance of the compression system. The pressure distortion sensitive coefficient of the compression system comprises 3 parameters: total pressure distortion sensitivity coefficient alpha of compression system Z CDFS pressure distortion sensitivity coefficient alpha CF Pressure distortion sensitive coefficient alpha of gas compressor C . The data required to calculate these 3 parameters include: the inlet comprehensive distortion index, the uniform flow characteristic, the distortion flow characteristic and the working line. Wherein, the inlet comprehensive distortion index, the uniform flow characteristic and the distortion flow characteristic are obtained by the test. The working line is obtained by matching the engine performance, and the invention is not described again. The working point is the intersection point of the working line and the characteristic line. The uniform flow and distortion flow characteristics and the working line are schematically shown in FIG. 3, the abscissa W c The conversion flow is shown, the ordinate pi shows the total pressure ratio, (1) a uniform flow characteristic surge point (2), a uniform flow working point (3), a distortion flow characteristic surge point (4) and a distortion flow working point.
The step of calculating the pressure distortion sensitivity coefficient in the step S3 is as follows:
s3.1: calculating the stability margin SM under uniform air intake conditions un i
SM uni ＝(π 1 /W c1 )/(π 2 /W c2 ) -1
Wherein, pi 1 Surge ratio, W, for uniform flow characteristics c1 Converting the flow rate for the surge point of the uniform flow characteristic; pi 2 Is a uniform flow operating point pressure ratio, W c2 Converting the flow rate for the uniform flow operating point;
s3.2: calculating the stability margin SM under distorted air intake conditions uni
SM dis ＝(π 3 /W c3 )/(π 4 /W c4 ) -1
Wherein, pi 3 The asthma-point pressure ratio, W, being of the distorted flow characteristics c3 Converted flow rate of surge point for distorted flow characteristics, pi 4 Is the distortion flow operating point pressure ratio, W c4 Converting the flow for the distortion flow working point;
s3.3: calculating the pressure distortion sensitivity coefficient alpha
Wherein,
is the inlet integrated distortion index.
In the above embodiment, the press variable sensitivity coefficient alpha of the compression system is calculated Z While, SM uni And SM dis Calculated according to S3.1 and S3.2 respectively from the working line and characteristics of the compression system, corresponding
For CDFS import composite distortion index
Pressure distortion sensitivity coefficient alpha in CDFS calculation CF When, SM uni And SM dis Calculated from the CDFS working line and characteristic as S3.1 and S3.1, respectively, corresponding to
For CDFS import composite distortion index
In the calculation of the pressure distortion sensitivity coefficient alpha of the compressor C While, SM uni And SM dis Calculated according to S3.1 and S3.1 respectively from the working line and characteristics of the compressor, corresponding
For the comprehensive distortion index of the inlet of the compressor
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, it is possible to make various improvements and modifications without departing from the technical principle of the present invention, and those improvements and modifications should be also considered as the protection scope of the present invention.
Claims (9)
1. A method for determining a pressure distortion sensitivity coefficient of a compression system, wherein the compression system comprises a core engine driving fan and a compressor, the method comprising the steps of:
s1: designing a distortion generating device;
s2: placing a core machine driving fan and a gas compressor in a compression system, and respectively obtaining the compression system, the core machine driving fan in the compression system and the pneumatic performance parameters of the gas compressor in the compression system;
s3: and calculating the sensitivity coefficients of the compression system, the core machine driving fan and the air compressor respectively through the pneumatic performance parameters obtained in the step S2.
2. The method for determining the pressure distortion sensitivity coefficient of a compression system as claimed in claim 1, wherein the distortion generating device in S1 is a fan-shaped insert plate structure.
3. The method for determining the pressure distortion sensitivity coefficient of a compression system as claimed in claim 2, wherein the fan angle θ of the fan-shaped insert plate structure is 150 ° -180 °; the thickness of the fan-shaped inserting plate is 10-20mm; the insertion depth L of the fan-shaped inserting plate is 0.1D-0.5D, wherein D is the diameter of an air inlet channel of the compression system.
4. The method of claim 3 wherein the insert plate is installed 2D-3D upstream of the core engine driven fan inlet during the test.
5. The method of claim 1, wherein the step of obtaining the aerodynamic performance of the compression system comprises:
a) Keeping the original regulation rule unchanged, wherein the regulation rule comprises the angle beta of the CDFS inlet guide vane CF0 Inlet guide vane angle beta of gas compressor C0 And a bypass ratio B 0 ；
b) Carrying out a uniform flow test, and measuring the pneumatic performance parameters of the compression system;
c) Inserting the distortion generating device into the air inlet channel, performing distortion flow test, and measuring the flow pressure ratio characteristic of the compression system and the comprehensive distortion index of the inlet of the compression system
6. The method of claim 5, wherein each characteristic line is not less than 6 points and ensures that a complete characteristic line can be formed when measuring the aerodynamic performance parameters of the compression system in a uniform flow test.
7. The method for determining the pressure distortion sensitivity coefficient of a compression system as claimed in claim 5, wherein the step of obtaining the aerodynamic performance of the core engine driven fan in the compression system is as follows:
a: keeping the original regulation rule unchanged, developing a uniform flow test, and measuring the flow pressure ratio characteristic of the core machine driving fan;
b: in the surge point parameter measuring process, if the gas compressor is unstable at first, the angle of the inlet guide vane of the gas compressor is reduced by 0.5 degrees, and meanwhile, the angle is reduced by 0.1B 0 The bypass ratio of (a);
c: repeating the step B) until the core machine driving fan is firstly unstable, and recording the inlet guide vane angle beta of the gas compressor at the moment C1 And bypass ratio B 1 And measuring asthma point parameters;
d: if the guide vane angle and the duct ratio are still unstable firstly when the limiting boundary is reached, the pressure distortion sensitive coefficient of the core engine driving fan in the system is zero, and the distortion flow test is not carried out any more;
e: maintenance of beta CF0 、β C1 、B 1 The regulation rule of the core machine driving fan is not changed, a distortion flow test is carried out, and the flow pressure ratio characteristic of the core machine driving fan and the comprehensive distortion index of the inlet of the core machine driving fan are measured
8. The method of determining a pressure distortion sensitivity coefficient of a compression system as set forth in claim 7, wherein the step of obtaining the aerodynamic performance of a compressor in the compression system is as follows:
a) Keeping the original regulation rule unchanged, carrying out a uniform flow test, and measuring the flow pressure ratio characteristic of the gas compressor;
b) In the surge point parameter measuring process, if the core machine driving fan is unstable at first, the angle of the inlet guide vane of the core machine driving fan is reduced by 0.5 degrees, and the angle of the inlet guide vane of the core machine driving fan is increased by 0.1B 0 A bypass ratio of (c);
c) Repeating the step b) until the compressor is firstly instable, and recording the inlet guide vane angle beta of the core machine driving fan at the moment CF1 And bypass ratio B 2 And measuring asthma point parameters;
d) If the fan is still driven by the core engine to be unstable when the guide vane angle and the duct ratio reach the limit boundary, the pressure distortion sensitive coefficient of the compressor in the system is zero, and the distortion flow test is not carried out any more;
e) Retention of beta CF0 、β CF1 、B 2 The regulation rule of the pressure sensor is not changed, a distortion flow test is carried out, the flow pressure ratio characteristic of the air compressor and the comprehensive distortion index of the inlet of the air compressor are measured
9. The method for determining the pressure distortion sensitivity coefficient of the compression system as claimed in claim 1, wherein the step of calculating the pressure distortion sensitivity coefficient in S3 is as follows:
s3.1: calculating the stability margin SM under uniform air intake conditions uni
SM uni ＝(π 1 /W c1 )/(π 2 /W c2 ) -1
Wherein, pi 1 Surge ratio, W, for uniform flow characteristics c1 Converting the flow rate for the surge point of the uniform flow characteristic; pi 2 Is a uniform flow operating point pressure ratio, W c2 Converting the flow rate for the uniform flow operating point;
s3.2: calculating the stability margin SM under distorted intake conditions uni
SM dis ＝(π 3 /W c3 )/(π 4 /W c4 ) -1
Wherein, pi 3 The abnormal flow characteristic asthma-point pressure ratio, W c3 Converted flow rate of surge point for distorted flow characteristics, pi 4 Is the distortion flow operating point pressure ratio, W c4 Converting the flow for the distortion flow working point;
s3.3: calculating the pressure distortion sensitivity coefficient alpha
Wherein,
is the inlet integrated distortion index.
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| CN202211043475.XA CN115585153A (en) | 2022-08-29 | 2022-08-29 | Method for determining pressure distortion sensitive coefficient of compression system |
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