CN108254206B - State adjusting method for performance test of high-total-pressure-ratio multistage compressor - Google Patents
State adjusting method for performance test of high-total-pressure-ratio multistage compressor Download PDFInfo
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Abstract
The invention relates to a state adjusting method for a performance test of a high-total-pressure-ratio multistage compressor, which realizes the control of the test working state of the compressor by the combined cooperative adjustment of four physical parameters of the rotating speed of the compressor, the adjustable stationary blade angle of the compressor, the opening of an air inlet throttle valve of a tester and the opening of an air exhaust throttle valve of the tester; controlling the working state of the compressor in the area near the plugging point of each equal-speed working line to carry out speed increasing and speed reducing operations; when the plurality of rows of stationary blades are singly adjusted, a method of sequentially adjusting from back to front when the rotating speed is increased and sequentially adjusting from front to back when the rotating speed is decreased is adopted, so that the requirement of optimizing and adjusting the matching rule between the lower stages of the non-designed rotating speed of the gas compressor is met; the invention reasonably utilizes the flow resistance of the air inlet throttle valve of the air compressor tester, reduces the power consumption of the air compressor by inlet throttling, and simultaneously realizes real-time accurate regulation and control of the working state of the air compressor by performing combined matching regulation with the exhaust throttle valve of the tester.
Description
Technical Field
The invention relates to the field of aerodynamic performance test research of aviation engine axial flow compressor components, is suitable for variable working condition performance tests of a civil aircraft high bypass ratio turbofan engine high total pressure ratio multistage axial flow compressor, which are developed on a ground open air suction type compressor tester, and provides a state adjusting method for the high total pressure ratio multistage compressor performance tests.
Background
The high total pressure ratio multistage axial flow compressor is a core compression component of a civil aircraft turbofan engine with a large bypass ratio, and the design total pressure ratio of the high total pressure compressor is far higher than that of a military low bypass ratio turbofan engine. The gas compressor test piece has the characteristics of high driving power, high exhaust pressure and temperature, multiple adjustable stationary blade stages, complex stage matching rule and the like, so that the pneumatic design and performance debugging of the high-total-pressure-ratio multistage gas compressor have high technical difficulty, and simultaneously, high technical requirements are provided for the comprehensive test capability and the test method of the gas compressor test piece. At present, the development work of a multistage axial flow compressor with a total pressure ratio close to 20 is still at a starting stage in China, the technical reserve is seriously insufficient, and compared with the advanced level in foreign countries, the comprehensive technical gap is very obvious.
Aiming at a conventional multistage axial flow compressor with a single row or multiple rows of stationary blade angles adjustable, when a performance test is performed on the conventional multistage axial flow compressor in China, a test state control method of joint adjustment of rotating speed, stationary blade angles and exhaust throttle valves is mostly adopted, namely, the exhaust throttle valves of a tester are fixed at a certain opening position, and the adjustable stationary blade angles are synchronously adjusted and controlled according to a given stationary blade angle adjusting rule of the compressor while the working rotating speed of the compressor is changed; after the gas compressor reaches the target rotating speed, the angle change of the stationary blade is kept, the back pressure of the outlet of the gas compressor is changed by adjusting the opening position of the exhaust throttle valve, so that the working state of the gas compressor is changed along a constant rotating speed working line, and finally the measurement of the constant rotating speed working characteristic curve of the gas compressor is completed. When the condition adjusting method is adopted to carry out a high total pressure ratio multistage compressor performance test, as the stage matching of the non-designed rotating speed (particularly the medium and low rotating speeds far away from the designed rotating speed) of the compressor is particularly sensitive to the angle of the static blade and the position of the working point, when the three parameters of the rotating speed, the angle of the static blade and the position of the working point are not matched, the compressor is very easy to enter an unstable working state such as rotating stall or surge, and the like, and the surge energy after the instability of the high total pressure ratio multistage compressor is usually larger, when an exhaust throttle valve is opened emergently, the compressor cannot exit the unstable working state in a short time, thereby bringing serious harm to the safe operation of a compressor.
The foreign advanced aeroengine research institutions (such as NASA, GE and Puhui companies in the United states; Roro company in the United kingdom; MTU and Anecom company in Germany; CIAM in Russia and the like) have gas compressor testers with strong test functions, accumulate abundant engineering experience in the aspect of performance test debugging of high total pressure ratio multistage gas compressors, successively develop a plurality of high-pressure gas compressors with excellent all-condition performance, and are applied to a plurality of civil large-bypass-ratio turbofan engine models (such as E3 ten-stage high-pressure gas compressors in the GE company, six-stage high-pressure gas compressors developed by the Puhui company for PW6000 engines and the like). Aiming at the performance test state adjustment control method of the high-total-pressure-ratio multistage compressor, at present, detailed description of related content information is not found through technical novelty retrieval, literature retrieval and other ways.
Disclosure of Invention
The purpose of the invention is as follows: on the basis of the test state adjustment control method of the existing multistage axial flow compressor in China, aiming at the special typical technical characteristics of the high total pressure ratio multistage compressor of a civil aircraft turbofan engine with a large bypass ratio, the state adjustment method suitable for the performance test of the high total pressure ratio multistage compressor is provided, the requirements of the pneumatic performance of the compressor on the angle of a static blade and the position sensitivity of a working point under the non-designed rotating speed are met, the smooth development of the variable working condition performance optimization test of the high total pressure ratio multistage compressor is ensured, the technical risk of the test debugging operation of the high total pressure ratio multistage compressor is reduced, and the success rate and the efficiency of the test research work of the compressor are improved.
The technical scheme of the invention is as follows: in order to achieve the above object, the technical solution of the present invention is as follows:
a state adjusting method for a high-total-pressure-ratio multistage compressor performance test realizes control of a compressor test working state through combined cooperative adjustment of four physical parameters of the compressor rotation speed, the adjustable stationary blade angle of the compressor, the opening of a tester air inlet throttle valve and the opening of a tester exhaust throttle valve.
The state adjusting method for the performance test of the high-total-pressure-ratio multistage compressor comprises the following steps of:
step 2, increasing the rotating speed of the compressor to a target rotating speed;
step 3, performing performance recording at a target rotating speed;
and 4, reducing the rotating speed.
The state adjusting method for the performance test of the high-total-pressure-ratio multistage compressor comprises the following steps of 2:
step 2.1, adjusting the angle of the adjustable stationary blade of the gas compressor in real time according to a preset control rule that the angle of the adjustable stationary blade of the gas compressor changes along with the rotating speed;
2.2, in the process of increasing the rotating speed, when the consumed power of the gas compressor reaches a power driving power limit value of the tester, adjusting the position of an air inlet throttle valve of the tester to throttle;
step 2.3, when the working point position of the gas compressor deviates from the working line blockage point of the calculated equal rotating speed, adjusting the position of the exhaust throttle valve of the tester to ensure that the heat insulation efficiency of the working point of the gas compressor is not lower than 50 percent;
the state adjusting method for the performance test of the high-total-pressure-ratio multistage compressor comprises the following steps of 3:
step 3.1, maintaining the target rotating speed and keeping the angle of the adjustable stationary blade unchanged;
step 3.2, gradually closing the opening of the exhaust throttle valve of the tester to perform constant-speed working characteristic curve recording, so that the working point of the gas compressor is changed from the blockage point of the constant-speed working line to the stable working boundary;
3.3, after the gas compressor reaches a stable working boundary, quickly opening an exhaust throttle valve of the tester to relieve surge, and ensuring that the working point of the gas compressor returns to the vicinity of a blocking point of a working line with equal rotating speed;
the state adjusting method for the performance test of the high-total-pressure-ratio multistage compressor comprises the following steps of (4):
step 4.1, adjusting the angle of the adjustable stationary blade along with the change of the rotating speed to perform follow-up adjustment;
and 4.2, gradually opening the air inlet throttle valve of the tester and the air exhaust throttle valve of the tester along with the reduction of the rotating speed, and ensuring that the working point position of the air compressor is always close to the blockage point of the working line with the equal rotating speed.
When multiple rows of static blades are singly adjusted, feedback parameters for controlling the angle of each row of static blades need to be independently adjusted, and the step 2.1 further comprises the following steps: and sequentially adjusting the angle of the adjustable stationary blade of each row of the gas compressor from the rear stage to the front stage in real time according to a preset control rule that the angle of the adjustable stationary blade of the gas compressor changes along with the rotating speed.
When multiple rows of static blades are singly adjusted, feedback parameters for controlling the angle of each row of static blades need to be independently adjusted, and the step 4.1 further comprises the following steps: the angle of the adjustable stationary blade is adjusted along with the change of the rotating speed, and the adjustment sequence is performed from the front stage to the rear stage in sequence.
In the step 3.2, when the opening of the exhaust throttle valve of the tester cannot accurately position the working point of the compressor in time, the opening of the inlet throttle valve of the tester is adjusted to assist the exhaust throttle valve of the tester to carry out combination matching adjustment.
The invention has the beneficial effects that: the invention provides a state adjusting method suitable for a performance test of a civil aircraft large-bypass-ratio turbofan engine high-total-pressure-ratio multistage compressor component. The state adjusting method provided by the invention has been fully verified in the performance test of the air compressor for many times, and the verification effect shows that: the state adjusting method effectively makes up the limitations of the traditional multistage compressor state adjusting method, remarkably relieves and improves the sudden stall and surge phenomena in the speed increasing and reducing processes of the multistage compressor with the high total pressure ratio, powerfully reduces the operation risk of the compressor test, and ensures the smooth development of the performance test research work.
The method is suitable for the requirement of developing the performance test research of the civil aircraft high total pressure ratio multistage air compressor on the ground open air suction type air compressor tester, is simple and easy to operate, fills up the domestic related technical blank, has higher popularization and application values in the development of domestic advanced civil aircraft large bypass ratio turbofan engines, and is expected to produce better economic and social benefits in the field of the development of domestic civil aircraft large bypass ratio turbofan engines.
Drawings
FIG. 1 is a flow chart of a test state adjusting method of a multi-row stationary blade combined high total pressure ratio multi-stage compressor in the invention;
FIG. 2 is a flow chart of a multi-row stator vane single high total pressure ratio multi-stage compressor test state adjusting method in the invention.
The specific implementation mode is as follows:
the present invention will be described in further detail below by way of specific embodiments:
the state adjusting method for the high total pressure ratio multistage compressor performance test totally relates to four adjusting parameters: the device comprises a gas compressor rotating speed, a gas compressor adjustable stationary blade angle, a tester air inlet throttle valve opening and an exhaust throttle valve opening. In the test process, the matching working state of the air compressor is accurately controlled in real time by combining and cooperatively adjusting the four physical parameters. The adjustable stationary blade angle is divided into the following two conditions according to the specific structure difference of the compressor test piece: multiple rows of vanes are jointly adjusted and multiple rows of vanes are individually adjusted. When multiple rows of static blades are adjusted in a combined mode, the ratio relation of the angles of the adjustable static blades of each row is determined by the static blade angle adjusting linkage mechanism of the gas compressor, and for test operation, only any one row of static blade angle feedback parameters need to be controlled. When the multiple rows of stationary blades are individually adjusted, feedback parameters for controlling the angle of each row of stationary blades need to be adjusted simultaneously. Aiming at the sensitivity problem of pneumatic matching between the non-designed rotating speed lower stages of the high total pressure ratio multistage compressor to the angle of the adjustable stationary blade and the position of the working point, the working state of the compressor is controlled in the region near the plugging point of each equal-rotating-speed working line to carry out speed increasing and speed reducing operations. Aiming at the problems that a plurality of rows of fixed blade monotonous compressors have more regulation and control parameters and the fixed blade angle is difficult to follow in real time, a strategy of sequentially adjusting from back to front when the rotating speed is increased and sequentially adjusting from front to back when the rotating speed is decreased is adopted according to the research result of the variable working condition interstage matching characteristic of the high total pressure ratio multistage compressor. Aiming at the problems of high driving power and high exhaust parameters of a high total pressure ratio multistage compressor, the flow resistance function of an air inlet throttle valve of a compressor tester is reasonably utilized, and the real-time accurate regulation and control of the working state of the compressor are realized by combining, matching and adjusting with an exhaust throttle valve of the tester while inlet throttling reduces the power consumption of the compressor.
The following two embodiments are specific application modes of the method under the conditions of multi-row stationary blade linkage and multi-row stationary blade monotony respectively:
a) the technical scheme of the test state adjusting method for the multi-row stationary blade combined high total pressure ratio multi-stage compressor is as follows:
1) before the test, the air inlet throttle valve and the exhaust throttle valve of the tester are both arranged at full-open positions;
2) in the speed-up process of the gas compressor, real-time adjustment is carried out according to the preset rule that the angle of the adjustable stationary blade changes along with the rotating speed; when the consumed power of the gas compressor reaches a power driving power limit value of the tester, the position of an air inlet throttle valve of the tester is adjusted to throttle, and the throttling degree is determined according to the air inlet Reynolds number of the gas compressor (the air inlet Reynolds number is ensured to be larger than the critical Reynolds number); when the working point position of the gas compressor deviates from the calculated equal-speed working line plugging point, the position of the exhaust throttle valve of the tester is adjusted to ensure that the heat insulation efficiency of the working point of the gas compressor is not lower than 50%;
3) when the air compressor reaches the target rotating speed, keeping the angle of the adjustable stationary blade unchanged, gradually closing the opening of the exhaust throttle valve of the tester to perform constant-rotating-speed working characteristic curve recording (if necessary, the specific position of the working point of the air compressor can be controlled by closing the opening of the intake throttle valve); after the gas compressor reaches a stable working boundary, the gas compressor is relieved of surge by quickly opening the exhaust throttling valve, and the working point of the gas compressor is ensured to return to the position near the plugging point of the working line with the equal rotating speed;
4) in the speed reduction process of the air compressor, the angle of the adjustable stationary blade is adjusted along with the change of the rotating speed, and meanwhile, the air inlet throttle valve and the air outlet throttle valve of the tester are opened gradually along with the reduction of the rotating speed, so that the working point position of the air compressor is always close to the plugging point of each equal-rotating-speed working line.
b) The technical scheme of the test state adjusting method of the multi-row stationary blade single-high total pressure ratio multi-stage compressor is expressed as follows:
1) before the test, the air inlet throttle valve and the exhaust throttle valve of the tester are both arranged at full-open positions;
2) in the process of accelerating the gas compressor, the gas compressor is adjusted from the rear stage to the front stage in sequence according to the preset rule that the angle of the adjustable stationary blade changes along with the rotating speed (namely according to S)n＞Sn-1＞S1＞S0The order of (d); when the consumed power of the gas compressor reaches a power driving power limit value of the tester, the position of an air inlet throttle valve of the tester is adjusted to throttle, and the throttling degree is determined according to the air inlet Reynolds number of the gas compressor (the air inlet Reynolds number is ensured to be larger than the critical Reynolds number); when the working point position of the gas compressor deviates from the calculated equal-speed working line plugging point, the position of the exhaust throttle valve of the tester is adjusted to ensure that the heat insulation efficiency of the working point of the gas compressor is not lower than 50%;
3) when the air compressor reaches the target rotating speed, keeping the angle of the adjustable stationary blade unchanged, gradually closing the opening of the exhaust throttle valve of the tester to perform constant-rotating-speed working characteristic curve recording (if necessary, the specific position of the working point of the air compressor can be controlled by closing the opening of the intake throttle valve); after the gas compressor reaches a stable working boundary, the gas compressor is relieved of surge by quickly opening the exhaust throttling valve, and the working point of the gas compressor is ensured to return to the position near the plugging point of the working line with the equal rotating speed;
4) in the process of the speed reduction of the gas compressor, the angle of the adjustable stationary blade is adjusted along with the change of the rotating speed, and the adjustment sequence is from the front stage to the rear stage (namely according to S)0＞S1＞Sn-1＞SnThe order of the first row of adjustable stationary blade angles is guaranteed in a key way if the multistage adjustable stationary blade angles lag behind the rotating speed change condition; meanwhile, the air inlet throttle valve and the air exhaust throttle valve of the tester are gradually opened along with the reduction of the rotating speed, so that the working point position of the air compressor is always close to the plugging point of each equal-rotating-speed working line.
Claims (6)
1. A state adjusting method for a performance test of a high-total-pressure-ratio multistage compressor is characterized in that the control of the test working state of the compressor is realized by the combined cooperative adjustment of four physical parameters of the rotating speed of the compressor, the adjustable stationary blade angle of the compressor, the opening of an air inlet throttle valve of a tester and the opening of an air outlet throttle valve of the tester; the method comprises the following steps:
step 1, arranging an air inlet throttle valve and an exhaust throttle valve of a tester at full-open positions;
step 2, increasing the rotating speed of the air compressor to a target rotating speed, specifically:
step 2.1, adjusting the angle of the adjustable stationary blade of the gas compressor in real time according to a preset control rule that the angle of the adjustable stationary blade of the gas compressor changes along with the rotating speed;
2.2, in the process of increasing the rotating speed, when the consumed power of the gas compressor reaches a power driving power limit value of the tester, adjusting the position of an air inlet throttle valve of the tester to throttle;
step 2.3, when the working point position of the gas compressor deviates from the working line blockage point of the calculated equal rotating speed, adjusting the position of the exhaust throttle valve of the tester to ensure that the heat insulation efficiency of the working point of the gas compressor is not lower than 50 percent;
step 3, performing performance recording at a target rotating speed;
and 4, reducing the rotating speed.
2. The condition adjusting method for the high-total-pressure-ratio multistage compressor performance test according to claim 1, wherein the step 3 further comprises the following steps:
step 3.1, maintaining the target rotating speed and keeping the angle of the adjustable stationary blade unchanged;
step 3.2, gradually closing the opening of the exhaust throttle valve of the tester to perform constant-speed working characteristic curve recording, so that the working point of the gas compressor is changed from the blockage point of the constant-speed working line to the stable working boundary;
and 3.3, after the gas compressor reaches a stable working boundary, quickly opening an exhaust throttle valve of the tester to relieve surge, and ensuring that the working point of the gas compressor returns to the position near the blockage point of the working line with the equal rotating speed.
3. The condition adjusting method for the high-total-pressure-ratio multistage compressor performance test is characterized in that the step 4 further comprises the following steps of:
step 4.1, adjusting the angle of the adjustable stationary blade along with the change of the rotating speed to perform follow-up adjustment;
and 4.2, gradually opening the air inlet throttle valve of the tester and the air exhaust throttle valve of the tester along with the reduction of the rotating speed, and ensuring that the working point position of the air compressor is always close to the blockage point of the working line with the equal rotating speed.
4. The condition adjusting method for the high total pressure ratio multistage compressor performance test according to claim 1, wherein when the multiple rows of stationary vanes are individually adjusted, feedback parameters for controlling the angle of each row of stationary vanes need to be individually adjusted, and the step 2.1 further includes: and sequentially adjusting the angle of the adjustable stationary blade of each row of the gas compressor from the rear stage to the front stage in real time according to a preset control rule that the angle of the adjustable stationary blade of the gas compressor changes along with the rotating speed.
5. A condition adjustment method for a high total pressure ratio multistage compressor performance test according to claim 3, wherein when the multiple rows of stationary vanes are individually adjusted, feedback parameters for controlling the angle of each row of stationary vanes need to be individually adjusted, and the step 4.1 further includes: the angle of the adjustable stationary blade is adjusted along with the change of the rotating speed, and the adjustment sequence is performed from the front stage to the rear stage in sequence.
6. The condition adjusting method for the performance test of the high-total-pressure-ratio multistage compressor is characterized in that in the step 3.2, when the opening of the exhaust throttle valve of the tester cannot accurately position the working point of the compressor in time, the opening of the inlet throttle valve of the tester is adjusted to assist the exhaust throttle valve of the tester to carry out combination matching adjustment.
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