CN112253523A - Test method and tester for identifying stall initial stage of multistage axial flow compressor - Google Patents
Test method and tester for identifying stall initial stage of multistage axial flow compressor Download PDFInfo
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- CN112253523A CN112253523A CN202011420401.4A CN202011420401A CN112253523A CN 112253523 A CN112253523 A CN 112253523A CN 202011420401 A CN202011420401 A CN 202011420401A CN 112253523 A CN112253523 A CN 112253523A
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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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/83—Testing, e.g. methods, components or tools therefor
Abstract
The invention provides a test method and a tester for identifying the stall initial stage of a multistage axial flow compressor, wherein the stage number of the multistage axial flow compressor is M and is a positive integer; the method comprises the following steps: carrying out a compressor surge-forcing test under the designed bleed air condition of the compressor to obtain surge margins of the compressor at a plurality of rotating speeds under the condition; under a specific rotating speed S1, respectively adjusting the opening degree of flow regulating valves of bleed air pipelines of an N1 stage and an N2 stage of the compressor, respectively increasing the bleed air quantity of an N1 stage and an N2 stage to carry out a surge-forcing test, and respectively obtaining surge margins SM1 and SM 2; n2 is more than N1 and less than or equal to M, and N2 is not adjacent to N1; respectively obtaining surge margin variation delta SM1 and delta SM2 according to the reference surge margin of the compressor at a specific rotating speed under a designed bleed air condition and the surge margins SM1 and SM 2; obtaining the position range of the stalling initial stage of the compressor according to comparison between delta SM1 and delta SM2 and zero values; the method and the device can obviously reduce the number of times of surge in the test process, improve the test efficiency and obtain a reliable judgment result.
Description
Technical Field
The invention mainly relates to the field of aircraft engines, in particular to a test method for identifying a stall initial stage of a multistage axial flow compressor and a compressor tester.
Background
Rotating stall and surge are two typical pneumatic instability phenomena of an engine compressor, and the pneumatic instability not only seriously restricts the improvement of the performance of the engine, but also is a working state which must be avoided by the engine. The stable working margin is used as an important assessment index of the gas compressor and is a key parameter obtained in a gas compressor performance test. A great deal of research is carried out at home and abroad aiming at the identification, monitoring or prediction of stall/surge in the process of a gas compressor test.
For a multistage axial-flow compressor, the surge margin cannot reach the expected index due to the multistage matching problem, which becomes a difficult point of pneumatic design of the compressor. In particular, when a partial low rotation speed surge margin occurs during the test and a local "pit" is present in the surge boundary (corresponding to a sudden decrease in the surge margin), the root cause of the problem cannot be identified, which makes design optimization difficult.
If the initial stage causing the stalling/surging of the compressor can be accurately judged in the test process, the method has important guiding significance for the optimization design of the compressor.
For the judgment of the stall/surge initial stage of the multistage axial-flow compressor, the existing research direction mainly focuses on monitoring of inter-stage pulsating pressure and signal processing, however, the development process of the pneumatic instability of the compressor is short, and the inter-stage pulsating pressure can be interfered by other excitation sources, so that the difficulty of accurately judging the stall initial stage is caused. In the process of developing the compressor, a test method or a test method for accurately identifying the stall/surge initial stage is needed.
Disclosure of Invention
The invention aims to provide a test method for identifying the stalling initial stage of a multistage axial flow compressor and a compressor tester, so that a reliable judgment result of the stalling initial stage of the multistage axial flow compressor is obtained, and the test efficiency and the feasibility are improved.
In order to solve the technical problem, the invention provides a test method for identifying a stall initial stage of a multistage axial flow compressor, wherein the stage number of the multistage axial flow compressor is M, M is a positive integer, and the method comprises the following steps:
performing a compressor surge-forcing test under the designed bleed air condition of the multistage axial flow compressor to obtain surge margins of the multistage axial flow compressor at a plurality of rotating speeds under the designed bleed air condition; under the specific rotating speed S1, adjusting the opening degree of a flow regulating valve of an N1 stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N1 stage by A1, performing a compressor surge test, and obtaining a first surge margin SM 1; n1 is less than or equal to M; n1 is a positive integer; under the specific rotating speed S1, adjusting the opening degree of a flow regulating valve of an N2 stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N2 stage by A2, performing a compressor surge test, and acquiring a second surge margin SM 2; n2 is less than or equal to M; n2 is a positive integer; n2 < N1 and N2 and N1 are not adjacent; obtaining surge margin variation delta SM1 and delta SM2 according to the reference surge margin of the multistage axial flow compressor at the specific rotating speed under the designed bleed air condition and the first surge margin SM1 and the second surge margin SM2 respectively; when the delta SM1 is less than or equal to 0 and the delta SM2 is less than or equal to 0, judging that the stalling initial stage of the multistage axial flow compressor at the specific rotating speed S1 is located at the rear stage of the Nth 1 stage; when the delta SM1 is larger than 0 and the delta SM2 is smaller than or equal to 0, judging that the stalling initial stage of the multistage axial flow compressor under the specific rotating speed S1 is located between the Nth 2 stage and the Nth 1 stage; and when the Delta SM1 is greater than 0 and the Delta SM2 is greater than 0, judging that the stall initial stage of the multistage axial flow compressor at the specific rotating speed S1 is located at the front stage of the Nth 2 stage.
In an embodiment of the present invention, the test method for identifying a stall initial stage of a multi-stage axial flow compressor further includes: obtaining surge margin variation of two adjacent or spaced stages in the rear stage of the Nth 1 stage or between the Nth 2 stage and the Nth 1 stage or in the front stage of the Nth 2 stage of the multistage axial flow compressor; and judging to obtain a stall initial stage of the multistage axial flow compressor at the specific rotating speed S1 according to the surge margin variation of the two adjacent stages or the two spaced stages.
In an embodiment of the present invention, after adjusting the opening degree of the flow regulating valve of the bleed air line of the nth 1 stage or the bleed air line of the nth 2 stage to change the bleed air amount of the corresponding stage, the surge margin of the corresponding stage is calculated by using the pressure ratio and the converted flow rate of different reference points, where the reference points are located on the common working line of the compressors.
In one embodiment of the invention, if interstage bleed air is not performed for a stage under compressor design bleed air conditions, the initial bleed air amount for that stage is set to zero.
In an embodiment of the invention, the multistage axial-flow compressor is divided into a front stage and a rear stage, the front stage performs air entrainment by adopting a negative pressure air entrainment mode, and the rear stage performs air entrainment by adopting a positive pressure air entrainment mode.
In an embodiment of the present invention, the relationship between the specific rotation speed S1 and the design rotation speed D is S1 = kxd; k is more than 0 and less than or equal to 1.05.
The invention also provides a compressor tester for identifying the stall initial stage of the multistage axial flow compressor, wherein the stage number of the multistage axial flow compressor is M, M is a positive integer, and the compressor tester comprises:
a controller configured to perform the steps of:
under the designed bleed air condition of the multistage axial flow compressor, controlling the compressor tester to carry out a compressor surge-forcing test, and obtaining surge margins of the multistage axial flow compressor at a plurality of rotating speeds under the designed bleed air condition; under the specific rotating speed S1, controlling the compressor tester to regulate the opening degree of a flow regulating valve of an N1-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N1-th stage by A1, and performing a compressor surge test to obtain a first surge margin SM 1; n1 is less than or equal to M; n1 is a positive integer; under the specific rotating speed S1, controlling the compressor tester to regulate the opening degree of a flow regulating valve of an N2-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N2-th stage by A2, and performing a compressor surge test to obtain a second surge margin SM 2; n2 is less than or equal to M; n2 is a positive integer; n2 < N1 and N2 and N1 are not adjacent; obtaining surge margin variation delta SM1 and delta SM2 according to the reference surge margin of the multistage axial flow compressor at the specific rotating speed under the designed bleed air condition and the first surge margin SM1 and the second surge margin SM2 respectively; when the delta SM1 is less than or equal to 0 and the delta SM2 is less than or equal to 0, judging that the stalling initial stage of the multistage axial flow compressor at the specific rotating speed S1 is located at the rear stage of the Nth 1 stage; when the delta SM1 is larger than 0 and the delta SM2 is smaller than or equal to 0, judging that the stalling initial stage of the multistage axial flow compressor under the specific rotating speed S1 is located between the Nth 2 stage and the Nth 1 stage; and when the Delta SM1 is greater than 0 and the Delta SM2 is greater than 0, judging that the stall initial stage of the multistage axial flow compressor at the specific rotating speed S1 is located at the front stage of the Nth 2 stage.
In an embodiment of the invention, the controller is further configured to perform the steps of:
obtaining surge margin variation of two adjacent or spaced stages in the rear stage of the Nth 1 stage or between the Nth 2 stage and the Nth 1 stage or in the front stage of the Nth 2 stage of the multistage axial flow compressor; and judging to obtain a stall initial stage of the multistage axial flow compressor at the specific rotating speed S1 according to the surge margin variation of the two adjacent stages or the two spaced stages.
Compared with the prior art, the invention has the following advantages: according to the test method for identifying the stall initial stage of the multistage axial flow compressor, the surge-approaching test of the compressor is carried out in a mode of changing the air entraining amount in a cross-stage mode at a specific rotating speed, the position range of the stall initial stage is judged and obtained according to the analysis of surge margin change, the surge entering times in the test process are obviously reduced, the test efficiency is improved, and a reliable judgment result is obtained, so that the design and optimization of the compressor are facilitated.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principle of the invention. In the drawings:
fig. 1 is a flowchart of a test method for identifying a stall initiation stage of a multi-stage axial flow compressor according to an embodiment of the present application.
Fig. 2 is an analysis diagram of surge margin calculation according to an embodiment of the application.
Fig. 3 is a flow chart of a test method of identifying a stall initiation stage of a multi-stage axial flow compressor according to another embodiment of the present application.
Fig. 4 is a schematic diagram of a positive pressure bleed air device of a compressor tester that identifies stall onset stages of a multi-stage axial flow compressor according to an embodiment of the present application.
Fig. 5 is a schematic diagram of a negative pressure bleed air device of a compressor tester for identifying a stall primary stage of a multi-stage axial flow compressor according to an embodiment of the present application.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways than those specifically described herein, and thus the present invention is not limited to the specific embodiments disclosed below.
Flow charts are used herein to illustrate operations performed by systems according to embodiments of the present application. It should be understood that the preceding or following operations are not necessarily performed in the exact order in which they are performed. Rather, various steps may be processed in reverse order or simultaneously. Meanwhile, other operations are added to or removed from these processes.
The embodiment of the application describes a test method for identifying a stall initial stage of a multistage axial flow compressor and a compressor tester. In some embodiments, the multistage axial compressor (or referred to as a multistage axial compressor) has M stages, where M is a positive integer. For example, the number of stages of the multistage axial flow compressor is 7, 8 or 10, and the multistage axial flow compressor is selected, designed and manufactured according to the requirements of the working environment of the compressor.
Fig. 1 is a flowchart of a test method for identifying a stall initiation stage of a multi-stage axial flow compressor according to an embodiment of the present application. As illustrated in fig. 1, the test method for identifying the stall initial stage of the multi-stage axial-flow compressor includes, in step 101, performing a compressor surge-forcing test under a designed bleed air condition of the multi-stage axial-flow compressor, and obtaining surge margins of the multi-stage axial-flow compressor at multiple rotation speeds under the designed bleed air condition. Step 102, under a specific rotating speed S1, adjusting the opening of a flow regulating valve of an N1-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N1-th stage by A1, performing a compressor surge test, and obtaining a first surge margin SM 1; n1 is less than or equal to M; n1 is a positive integer. 103, under a specific rotating speed S1, adjusting the opening of a flow regulating valve of an N2-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N2-th stage by A2, performing a compressor surge test, and obtaining a second surge margin SM 2; n2 is less than or equal to M; n2 is a positive integer; n2 < N1 and N2 and N1 are not adjacent. And step 104, respectively obtaining surge margin variation delta SM1 and delta SM2 according to the reference surge margin of the multi-stage axial flow compressor at the specific rotating speed under the designed bleed air condition and the first surge margin SM1 and the second surge margin SM 2. And 105, when the delta SM1 is less than or equal to 0 and the delta SM2 is less than or equal to 0, judging that the stalling initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 is located at the rear stage of the Nth 1 stage. And 106, when the delta SM1 is larger than 0 and the delta SM2 is smaller than or equal to 0, judging that the stalling initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 is located between the Nth 2 stage and the Nth 1 stage. And step 107, when the Δ SM1 is greater than 0 and the Δ SM2 is greater than 0, judging that the stall initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 is located at the front stage of the Nth 2 stage.
Specifically, in step 101, a compressor surge-forcing test is performed under the designed bleed air condition of the multi-stage axial-flow compressor, and surge margins of the multi-stage axial-flow compressor at multiple rotation speeds under the designed bleed air condition are obtained. The designed air entraining condition of the multi-stage axial flow compressor is the initial air entraining amount of each stage in a plurality of stages with the interstage air entraining function in the compressor. Therefore, if the interstage bleed air is not conducted in a certain stage under the designed bleed air condition of the compressor, the initial bleed air quantity of the stage is set to be zero. The values of the plurality of rotational speeds may be selected according to requirements, for example, 30%, … …, 80%, 90%, 95%, 100%, etc. of the design rotational speed D, or may be slightly greater than the design rotational speed, for example, 101%, 102%, etc. of the design rotational speed. The design rotation speed D is, for example, 1.5 ten thousand revolutions per minute, 2 ten thousand revolutions per minute, or the like.
In step 102, under a specific rotating speed S1, the opening degree of a flow regulating valve of an N1 stage bleed air pipeline of the multistage axial flow compressor is regulated, so that the bleed air quantity of an N1 stage bleed air is increased by A1, a compressor surge test is carried out, and a first surge margin SM1 is obtained. In one embodiment, N1 ≦ M and N1 is a positive integer. The relation of the specific rotation speed S1 design rotation speed D is S1 = k × D; k is more than 0 and less than or equal to 1.05.
In some embodiments, the surge margin is calculated as
Wherein the content of the first and second substances,
is the value of the pressure ratio at the common working line,
to the converted flow value at the common operating line,
the ratio of the surge point pressure to the surge point pressure,
the flow value is converted for the surge point. The common working line is a curve representing the matched working state of a compressor and a turbine of the engine. Fig. 2 is an analysis diagram of surge margin calculation according to an embodiment of the present application. Curve 201 in fig. 2 is the common working line. The dashed line 202 in fig. 2 is a schematic curve of the surge margin for the compressor under design bleed air conditions. Point 205 characterization in FIG. 2And designing the converted flow and the pressure ratio at the common working line under the condition of bleed air. Point 206 represents the scaled flow and pressure ratio at the surge point under design bleed air conditions. The point 207 represents a converted flow rate and pressure ratio value of a possible surge point a in the case that the bleed air quantity of the N1 th stage is increased by a1 by adjusting the opening degree of a flow regulating valve of the bleed air pipeline of the N1 th stage of the multistage axial flow compressor, that is, the bleed air quantity of the N1 th stage of the multistage axial flow compressor is increased. Point 208 represents the scaled flow and pressure ratio value for the possible surge point b. In the experiment, if the surge point obtained by the test is the surge point a corresponding to the point 208, the surge margin at the moment is larger than the surge margin under the designed bleed air condition. And if the surge point obtained by the test is the surge point b corresponding to the point 207, the surge margin at the moment is smaller than the surge margin under the designed bleed air condition.
The surge margin in the technical scheme of the application is the comprehensive margin of the conversion flow and the pressure ratio. The pressure ratio is the ratio of the total outlet pressure to the total inlet pressure of the compressor.
In step 103, under a specific rotating speed S1, adjusting the opening degree of a flow regulating valve of an N2-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N2-th stage by A2, performing a compressor surge test, and acquiring a second surge margin SM 2; n2 is less than or equal to M; n2 is a positive integer; n2 < N1 and N2 and N1 are not adjacent. The manner of calculation of the surge margin is as described above and is not repeated here.
In step 104, a surge margin variation delta SM1 and a surge margin delta SM2 are respectively obtained according to a reference surge margin of the multi-stage axial flow compressor at a specific rotating speed under the designed bleed air condition and the first surge margin SM1 and the second surge margin SM 2.
In one embodiment, for example, if the reference surge margin of the multistage axial flow compressor at a specific rotational speed under the designed bleed air conditions is SM0, the surge margin variations Δ SM1 and Δ SM2 are obtained according to the reference surge margin SM0 and the first surge margin SM1 and the second surge margin SM 2. For example Δ SM1 = SM 1-SM 0.Δ SM2 = SM 2-SM 0. It is also possible to multiply by a factor, for example Δ SM1 = k1 × (SM 1-SM 0), depending on the actual design situation. Δ SM2 = k2 × (SM 2-SM 0). The coefficients k1, k2 are, for example, positive or negative values, which may characterize magnitude and direction.
In the technical scheme of this application, adjust the bleed air volume of the flow control valve aperture change corresponding level of N1 level bleed air pipeline or N2 level bleed air pipeline after, use the pressure ratio of different reference points and the surge margin of conversion flow calculation corresponding level, the reference point is located on the common operating line 201 of compressor. Specifically, as shown in fig. 2, the value represented by the point 205 and the point 206 and the calculation formula of the surge margin described above can be used to obtain the magnitude of the surge margin under the designed bleed air conditions, and more specifically, the magnitude of the surge margin of the compressor at a specific rotation speed under the designed bleed air conditions, and the curve 203 is the characteristic curve corresponding to the rotation speed and the bleed air conditions.
Then, a test is performed to increase the bleed air volume at a certain stage of the multi-stage axial flow compressor, resulting in a possible surge point, for example, point 207 or point 208. In order to obtain the surge margin SM1 or SM2 at this time, the reference point is no longer the point 205 on the common working line when calculated by the above-described calculation formula. But rather a point 209 on the common work line. Although the rotating speed of the multistage axial-flow compressor is not changed, the flow of the compressor is changed due to the change of the bleed air quantity of a certain stage, so that the equal rotating speed characteristic line of the compressor is actually deviated. Therefore, a new characteristic line 204 needs to be drawn, and the intersection point between the characteristic line and the common working line, i.e. the point 209, is obtained as a new reference point. On the basis of this, the surge margin under the condition of the bleed air amount increase test is obtained. If the reference point is not updated and the point 203 is still used as the calculation reference point under the condition of the test for increasing the bleed air quantity, the calculated surge margin will deviate, which may cause errors in the test and the test result.
In step 105, when Δ SM1 is less than or equal to 0 and Δ SM2 is less than or equal to 0, it is determined that the stall initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 is located at the rear stage of the N1 th stage.
In step 106, when Δ SM1 is greater than 0 and Δ SM2 is less than or equal to 0, it is determined that the stall initial stage of the multi-stage axial flow compressor at the specific rotation speed S1 is located between the nth 2 stage and the nth 1 stage.
In step 107, when Δ SM1 is greater than 0 and Δ SM2 is greater than 0, it is determined that the stall initial stage of the multi-stage axial flow compressor at the specific speed S1 is located at the stage before the nth 2 stage.
In order to more specifically understand the method of the present application, taking a ten-stage axial flow compressor as an example, in the method for testing the stall initial stage of the multi-stage axial flow compressor of the present application, in step 101, under the condition of designing bleed air of the ten-stage axial flow compressor, a compressor surge-forcing test is performed to obtain the surge margin of the multi-stage axial flow compressor at multiple rotation speeds under the condition of designing bleed air. In step 102, under a specific rotating speed S1, the opening degree of a flow regulating valve of a 7 th stage bleed air pipeline of the ten-stage axial-flow compressor is regulated, so that the 7 th stage bleed air quantity is increased by A1, a compressor surge test is carried out, and a first surge margin SM1 is obtained. In step 103, under a specific rotating speed S1, the opening degree of a flow regulating valve of a 4 th stage bleed air pipeline of the ten-stage axial flow compressor is regulated, so that the 4 th stage bleed air quantity is increased by A2, a compressor surge test is carried out, and a first surge margin SM2 is obtained. In step 104, a surge margin variation delta SM1 and delta SM2 are obtained according to a reference surge margin of the ten-stage axial flow compressor at a specific rotating speed S1 under the designed bleed air condition and the first surge margin SM1 and the second surge margin SM2 respectively.
Then, in steps 105 to 107, according to different situations of the Δ SM1 and the Δ SM2, the stall initial stage of the ten-stage axial-flow compressor at the specific rotating speed S1 is judged to be located at the rear stage of the 7 th stage or between the 4 th stage and the 7 th stage or at the front stage of the 4 th stage.
As illustrated in fig. 3, in some embodiments, the technical solution of the present application may further include, in addition to the steps 101 to 107, a step 108 of obtaining a surge margin variation of two adjacent stages or intervals in a later stage of an nth 1 stage or between an nth 2 stage and an nth 1 stage of the multistage axial compressor or in an earlier stage of an nth 2 stage. And step 109, judging to obtain a stall initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 according to the surge margin variation of two adjacent stages or two spaced stages.
For example, in the ten-stage axial compressor exemplified above, after the steps 101 to 107, if it is determined that the stall initial stage is located at the stage subsequent to the 7 th stage, the surge margin variation of two adjacent stages or two spaced stages, for example, the 7 th stage and the 9 th stage, may be performed in the 7 th to 10 th stages. And then, judging to obtain the stall initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 according to the surge margin variation of two adjacent stages or two spaced stages. The manner of determination is similar to steps 105 to 107. For example, in one embodiment, the stall initiation stage of the ten-stage axial compressor at a specific speed S1, such as 95%, is stage 8.
In some embodiments, a multi-stage axial flow compressor may be divided into a forward stage and an aft stage. For example, for a ten-stage axial compressor, the first through fifth stages are divided into the preceding stages, and the sixth through tenth stages are divided into the following stages. Fore and aft are relative to the direction of airflow, e.g., along the flow of bleed air, with the forward stage being in the upstream direction and the aft stage being in the downstream direction. When the air entraining test is carried out, in order to ensure the air entraining amount of the front stage at the medium and low rotating speeds, the front stage adopts a negative pressure air entraining mode to carry out air entraining, and the rear stage adopts a positive pressure air entraining mode to carry out air entraining, so that the test for identifying the stalling initial stage of the multistage axial flow compressor can be effectively carried out, and the feasibility of the test is ensured.
According to the test method for identifying the stall initial stage of the multi-stage axial flow compressor, the surge-forcing test of the compressor is carried out in a mode of changing the air entraining amount in a cross-stage mode at a specific rotating speed, some stages which are possibly the stall initial stage are judged and obtained according to the analysis of surge margin change, the number of surge intake times in the test process is obviously reduced, the test efficiency is improved, and a reliable judgment result is obtained, so that the design and optimization of the compressor are facilitated.
Then, whether to carry out further surge-approaching tests of two adjacent stages or two spaced stages from the preliminarily screened stages can be determined according to actual application requirements or test conditions of the compressor, and finally, a stall initial stage at a specific rotating speed is found. The technical scheme of the application has more remarkable significance under the condition that the range of the stall primary level or the stall primary level under multiple rotating speeds needs to be obtained, the test quantity is greatly reduced, a reliable judgment result is obtained, and the method, which is not a method for determining the stall primary level through measurement of inter-stage pulsating pressure, is easily interfered by other excitation sources.
The application also provides a gas compressor tester for identifying the stall initial stage of the multistage axial flow gas compressor. The multistage axial flow compressor has M stages, wherein M is a positive integer.
In some embodiments of the present application, a compressor tester that identifies a stall initiation stage of a multi-stage axial flow compressor includes a controller. The controller is configured to execute the following steps, step 101, to perform a compressor surge-forcing test under the designed bleed air condition of the multi-stage axial flow compressor, and obtain surge margins of the multi-stage axial flow compressor at multiple rotation speeds under the designed bleed air condition. Step 102, under a specific rotating speed S1, adjusting the opening of a flow regulating valve of an N1-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N1-th stage by A1, performing a compressor surge test, and obtaining a first surge margin SM 1; n1 is less than or equal to M; n1 is a positive integer. 103, under a specific rotating speed S1, adjusting the opening of a flow regulating valve of an N2-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N2-th stage by A2, performing a compressor surge test, and obtaining a second surge margin SM 2; n2 is less than or equal to M; n2 is a positive integer; n2 < N1 and N2 and N1 are not adjacent. And step 104, respectively obtaining surge margin variation delta SM1 and delta SM2 according to the reference surge margin of the multi-stage axial flow compressor at the specific rotating speed under the designed bleed air condition and the first surge margin SM1 and the second surge margin SM 2. And 105, when the delta SM1 is less than or equal to 0 and the delta SM2 is less than or equal to 0, judging that the stalling initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 is located at the rear stage of the Nth 1 stage. And 106, when the delta SM1 is larger than 0 and the delta SM2 is smaller than or equal to 0, judging that the stalling initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 is located between the Nth 2 stage and the Nth 1 stage. And step 107, when the Δ SM1 is greater than 0 and the Δ SM2 is greater than 0, judging that the stall initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 is located at the front stage of the Nth 2 stage.
In some embodiments, the controller may be further configured to perform the step of obtaining 108 surge margin variances of two adjacent stages or intervals in a later stage or stages N2 through N1 of the N1 th stage or a preceding stage of the N2 th stage of the multi-stage axial flow compressor. And step 109, judging to obtain a stall initial stage of the multi-stage axial flow compressor at the specific rotating speed S1 according to the surge margin variation of two adjacent stages or two spaced stages.
More specific procedures of steps 101 to 109 are as described above and will not be repeated here.
In an embodiment, the compressor tester for identifying the stall initial stage of the multi-stage axial flow compressor further comprises a power system, an air inlet system, an exhaust system, a bleed air system, an auxiliary air system, a hydraulic system, an oil system, a data acquisition system and the like.
The power system comprises equipment or components such as a power motor, a speed increaser, a torque measuring device and a coupler and is used for driving a gas compressor test piece and realizing the functions of rotating speed measurement, torque measurement, axial force balance and the like. The air inlet system is composed of an air inlet flow tube, an air inlet pipeline, an air inlet valve, a pressure stabilizing box, a rectifying screen, an expansion joint, a flow guide basin and other components and is used for providing a uniform air inlet flow field and realizing air inlet flow measurement, and the air inlet valve is used for adjusting air inlet pressure and simulating different Reynolds number conditions of an inlet of the air compressor or reducing the physical flow of the air compressor so as to reduce power. The exhaust system mainly comprises an exhaust gas collection chamber, an exhaust valve and an exhaust pipeline, wherein the exhaust valve is used for changing the back pressure of the gas compressor and comprises a main adjusting valve and a fine adjusting valve, so that the fine adjustment of the pressure ratio of the gas compressor is realized. The auxiliary air system, the hydraulic system and the lubricating oil system are auxiliary test equipment and provide lubricating oil for auxiliary air supply, hydraulic power source and bearing lubrication and cooling for the air compressor tester or the air compressor test piece. The controller can control an auxiliary air system, a hydraulic system, a lubricating oil system and the like, and adjusts the relative air inlet valve, exhaust valve, air guide valve, adjustable stationary blade actuating device, the rotating speed of the power motor and the like according to the working condition of the compressor, so as to realize the process of identifying the stalling initial stage of the multistage axial flow compressor.
According to the technical scheme, the multi-channel negative-pressure air extraction air guide device is arranged in the air guide system to improve the adjustable range of the air guide amount of the front stage of the air compressor at the medium-low rotating speed, and the multi-channel positive-pressure air guide device is arranged for air guide of the rear stage of the air compressor, so that the effective implementation of a test for identifying the stalling initial stage of the multi-stage axial flow air compressor can be realized, and the feasibility of the test is ensured.
As illustrated in fig. 4, the positive pressure bleed air device may include a bleed air collecting cavity 1.1, a bleed air pipeline 1.2, a flow regulating valve 1.3, an orifice plate flowmeter 1.4, a first pressure sensor 1.5, a second pressure sensor 1.6, a temperature sensor 1.7, a differential pressure sensor 1.8, and an ejector 1.9.
The air-entraining and air-collecting cavity 1.1 is connected with the air compressor test piece through a metal corrugated pipe and is used for converging a plurality of air-entraining holes of the air compressor test piece to one air-entraining pipeline 1.2; the flow regulating valve 1.3 is used for regulating the bleed air flow of the road; the orifice plate flowmeter 1.4 is used for measuring the flow of the bleed air; the first pressure sensor 1.5 and the second pressure sensor 1.6 measure the pressure before and after the flow regulating valve 1.3 respectively, wherein the pressure after the valve is used for calculating the induced flow; the temperature sensor 1.7 measures the temperature of the airflow in front of the orifice plate flowmeter and is used for calculating the induced airflow; the differential pressure sensor 1.8 measures the differential pressure of the orifice plate flowmeter and is used for calculating the flow of the bleed air; the ejector 1.9 is used for increasing the flow rate of exhaust gas, and is mixed with cold air in an ejection mode to achieve the purpose of exhaust gas cooling.
Figure 5 is a schematic view of a negative pressure bleed air arrangement. The negative pressure air-entraining device is composed of an air-entraining air-collecting cavity 2.1, an air-entraining pipeline 2.2, a flow regulating valve 2.3, an orifice plate flowmeter 2.4, a first pressure sensor 2.5, a second pressure sensor 2.6, a temperature sensor 2.7, a differential pressure sensor 2.8 and a back pressure regulating valve 2.9.
Wherein, the back pressure regulating valve 2.9 is used for regulating the back pressure of the negative pressure bleed air pipeline. It should be noted that reducing the back pressure is beneficial to improving the bleed air flow, but too low back pressure may cause insufficient adjustment accuracy of the flow adjusting valve under the working condition of small bleed air flow of the compressor, and the back pressure valve is arranged to improve the bleed air flow adjustment accuracy. The other components of the negative pressure bleed air device are similar to the corresponding components of the positive pressure bleed air device and are not repeated.
The technical scheme of the application is not simply to test the change of the air entrainment amount of a certain stage of the multistage axial flow compressor and observe the performance changes of the compressor and the engine at the moment, such as the operation efficiency of the compressor or the surge margin change at the moment, and the air entrainment amount test is only a conventional test.
According to the technical scheme, the surge-forcing test of the gas compressor is carried out in a mode of changing the air entraining amount in a cross-stage mode at a specific rotating speed, the range of the stall primary stage is judged and obtained according to the analysis of the surge margin change and the relation between the surge margin change and the position of the stall primary stage of the gas compressor, the surge frequency in the test process is obviously reduced, the test efficiency is improved, and a reliable judgment result is obtained, so that the design and optimization of the gas compressor are facilitated. And under the condition that the range of the stall primary level or the stall receiving level under a plurality of rotating speeds needs to be obtained, the significance is more remarkable, the test quantity is greatly reduced, a reliable judgment result is obtained, and the method for determining the stall primary level through measuring the inter-stage pulsating pressure is not easy to be interfered by other excitation sources.
This application uses specific words to describe embodiments of the application. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
Aspects of the present application may be performed by hardware, by software (including firmware, resident software, micro-code, etc.), or by a combination of hardware and software. The above hardware or software may be referred to as "data block," module, "" engine, "" unit, "" component, "or" system. The processor may be one or more Application Specific Integrated Circuits (ASICs), Digital Signal Processors (DSPs), digital signal processing devices (DAPDs), Programmable Logic Devices (PLDs), Field Programmable Gate Arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or a combination thereof. Furthermore, aspects of the present application may be represented as a computer product, including computer readable program code, embodied in one or more computer readable media. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disk, floppy disk, magnetic strips … …), optical disks (e.g., Compact Disk (CD), Digital Versatile Disk (DVD) … …), smart cards, and flash memory devices (e.g., card, stick, key drive … …).
Similarly, it should be noted that in the preceding description of embodiments of the application, various features are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure aiding in the understanding of one or more of the embodiments. This method of disclosure, however, is not intended to require more features than are expressly recited in the claims. Indeed, the embodiments may be characterized as having less than all of the features of a single embodiment disclosed above.
Although the present application has been described with reference to the present specific embodiments, it will be recognized by those skilled in the art that the foregoing embodiments are merely illustrative of the present application and that various changes and substitutions of equivalents may be made without departing from the spirit of the application, and therefore, it is intended that all changes and modifications to the above-described embodiments that come within the spirit of the application fall within the scope of the claims of the application.
Claims (12)
1. A test method for identifying a stall initial stage of a multistage axial flow compressor, wherein the stage number of the multistage axial flow compressor is M stages, and M is a positive integer, the method comprises the following steps:
performing a compressor surge-forcing test under the designed bleed air condition of the multistage axial flow compressor to obtain surge margins of the multistage axial flow compressor at a plurality of rotating speeds under the designed bleed air condition;
under the specific rotating speed S1, adjusting the opening degree of a flow regulating valve of an N1 stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N1 stage by A1, performing a compressor surge test, and obtaining a first surge margin SM 1; n1 is less than or equal to M; n1 is a positive integer;
under the specific rotating speed S1, adjusting the opening degree of a flow regulating valve of an N2 stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N2 stage by A2, performing a compressor surge test, and acquiring a second surge margin SM 2; n2 is less than or equal to M; n2 is a positive integer; n2 < N1 and N2 and N1 are not adjacent;
obtaining surge margin variation delta SM1 and delta SM2 according to the reference surge margin of the multistage axial flow compressor at the specific rotating speed under the designed bleed air condition and the first surge margin SM1 and the second surge margin SM2 respectively;
when the delta SM1 is less than or equal to 0 and the delta SM2 is less than or equal to 0, judging that the stalling initial stage of the multistage axial flow compressor at the specific rotating speed S1 is located at the rear stage of the Nth 1 stage;
when the delta SM1 is larger than 0 and the delta SM2 is smaller than or equal to 0, judging that the stalling initial stage of the multistage axial flow compressor under the specific rotating speed S1 is located between the Nth 2 stage and the Nth 1 stage; and
and when the Delta SM1 is greater than 0 and the Delta SM2 is greater than 0, judging that the stall initial stage of the multistage axial flow compressor at the specific rotating speed S1 is located at the front stage of the Nth 2 stage.
2. The testing method for identifying the stall initiation stage of the multi-stage axial flow compressor as claimed in claim 1, further comprising:
obtaining surge margin variation of two adjacent or spaced stages in the rear stage of the Nth 1 stage or between the Nth 2 stage and the Nth 1 stage or in the front stage of the Nth 2 stage of the multistage axial flow compressor; and
and judging to obtain a stall initial stage of the multistage axial flow compressor at the specific rotating speed S1 according to the surge margin variation of the two adjacent stages or the two spaced stages.
3. The test method for identifying the stall initiation stage of the multi-stage axial flow compressor as claimed in claim 1, wherein after adjusting the opening degree of the flow regulating valve of the bleed air pipeline of the N1 th stage or the bleed air pipeline of the N2 th stage to change the bleed air amount of the corresponding stage, the surge margin of the corresponding stage is calculated by using the pressure ratio and the converted flow rate of different reference points, wherein the reference points are located on the common working line of the compressor.
4. The test method for identifying the stall initiation stage of the multi-stage axial flow compressor according to claim 1, wherein if interstage bleed air is not performed for a stage under compressor design bleed air conditions, the initial bleed air amount for the stage is set to zero.
5. The test method for identifying the stall initial stage of the multi-stage axial flow compressor according to claim 1, wherein the multi-stage axial flow compressor is divided into a front stage and a rear stage, the front stage performs air entraining in a negative pressure air entraining manner, and the rear stage performs air entraining in a positive pressure air entraining manner.
6. The test method for identifying the stall initiation stage of the multi-stage axial flow compressor as claimed in claim 1, wherein the relation between the specific rotating speed S1 and the design rotating speed D is S1 = kxD; k is more than 0 and less than or equal to 1.05.
7. A compressor tester for identifying the stall initial stage of a multistage axial flow compressor, wherein the stage number of the multistage axial flow compressor is M stages, M is a positive integer, and the compressor tester comprises:
a controller configured to perform the steps of:
under the designed bleed air condition of the multistage axial flow compressor, controlling the compressor tester to carry out a compressor surge-forcing test, and obtaining surge margins of the multistage axial flow compressor at a plurality of rotating speeds under the designed bleed air condition;
under the specific rotating speed S1, controlling the compressor tester to regulate the opening degree of a flow regulating valve of an N1-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N1-th stage by A1, and performing a compressor surge test to obtain a first surge margin SM 1; n1 is less than or equal to M; n1 is a positive integer;
under the specific rotating speed S1, controlling the compressor tester to regulate the opening degree of a flow regulating valve of an N2-th stage bleed air pipeline of the multistage axial flow compressor, increasing the bleed air quantity of an N2-th stage by A2, and performing a compressor surge test to obtain a second surge margin SM 2; n2 is less than or equal to M; n2 is a positive integer; n2 < N1 and N2 and N1 are not adjacent;
obtaining surge margin variation delta SM1 and delta SM2 according to the reference surge margin of the multistage axial flow compressor at the specific rotating speed under the designed bleed air condition and the first surge margin SM1 and the second surge margin SM2 respectively;
when the delta SM1 is less than or equal to 0 and the delta SM2 is less than or equal to 0, judging that the stalling initial stage of the multistage axial flow compressor at the specific rotating speed S1 is located at the rear stage of the Nth 1 stage;
when the delta SM1 is larger than 0 and the delta SM2 is smaller than or equal to 0, judging that the stalling initial stage of the multistage axial flow compressor under the specific rotating speed S1 is located between the Nth 2 stage and the Nth 1 stage; and
and when the Delta SM1 is greater than 0 and the Delta SM2 is greater than 0, judging that the stall initial stage of the multistage axial flow compressor at the specific rotating speed S1 is located at the front stage of the Nth 2 stage.
8. The compressor tester for identifying a stall onset stage of a multi-stage axial flow compressor as recited in claim 7, wherein the controller is further configured to perform the steps of:
obtaining surge margin variation of two adjacent or spaced stages in the rear stage of the Nth 1 stage or between the Nth 2 stage and the Nth 1 stage or in the front stage of the Nth 2 stage of the multistage axial flow compressor; and
and judging to obtain a stall initial stage of the multistage axial flow compressor at the specific rotating speed S1 according to the surge margin variation of the two adjacent stages or the two spaced stages.
9. The compressor tester for identifying the stall primary stage of the multi-stage axial flow compressor as claimed in claim 7, wherein after adjusting the opening degree of the flow regulating valve of the bleed air pipeline of the Nth 1 stage or the bleed air pipeline of the Nth 2 stage to change the bleed air amount of the corresponding stage, the surge margin of the corresponding stage is calculated by using the pressure ratio and the converted flow rate of different reference points, wherein the reference points are located on the common working line of the compressor.
10. The compressor tester for identifying a stall initiation stage of a multi-stage axial flow compressor as recited in claim 7, wherein if a stage is not staged for bleed air under compressor design bleed air conditions, the initial bleed air quantity for the stage is set to zero.
11. The compressor tester for identifying the stall primary stage of the multi-stage axial flow compressor as claimed in claim 7, wherein the multi-stage axial flow compressor is divided into a front stage and a rear stage, the front stage performs air-entraining by means of negative pressure air-entraining, and the rear stage performs air-entraining by means of positive pressure air-entraining.
12. The compressor tester for identifying the stall initiation stage of the multi-stage axial compressor as claimed in claim 7, wherein the relationship between the specific rotation speed S1 and the design rotation speed D is S1 = kxD; k is more than 0 and less than or equal to 1.05.
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