CN112550758A - Method for obtaining actual performance of each part of engine under complete machine condition - Google Patents
Method for obtaining actual performance of each part of engine under complete machine condition Download PDFInfo
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- CN112550758A CN112550758A CN202011395117.6A CN202011395117A CN112550758A CN 112550758 A CN112550758 A CN 112550758A CN 202011395117 A CN202011395117 A CN 202011395117A CN 112550758 A CN112550758 A CN 112550758A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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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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Abstract
The application belongs to the field of aircraft engine tests and relates to a method for obtaining actual performances of all parts of an engine under the condition of a complete machine, which comprises the following steps: changing the working point of the fan by adjusting the area of the outlet of the external culvert to obtain the characteristics of the fan under the condition of the whole machine; carrying out angle adjustment tests of the fixed spray pipes and the adjustable guide vanes of the gas compressor with different areas to obtain the characteristics of the gas compressor under the condition of simulating the environment of the whole gas compressor; calculating the total pressure recovery coefficient of the main combustion chamber by adopting static pressure loss instead of total pressure loss, and obtaining the combustion efficiency of the main combustion chamber and the afterburner by analyzing the components of the gas; obtaining a low-pressure turbine expansion ratio according to the total expansion ratio of each rotating speed state and the culvert outlet pressure; the flow characteristics of the cooling air sealing structure, the pipelines and the nozzles of the turbine of the engine are obtained through tests, and further the air entraining amount of each flow path is determined. The method and the device can obtain the actual performance of each part in the working environment of the whole machine and the matching relation between the actual performance and the matching relation, and can provide important support for pneumatic stability evaluation.
Description
Technical Field
The application belongs to the field of aircraft engine tests, and particularly relates to a method for obtaining actual performances of all parts of an engine under the condition of a complete machine.
Background
At present, the main way for mastering the performance of each part of the aircraft engine is to develop part tests. However, due to the limitations of the equipment capability and the like, the component test is usually performed under the conditions of normal temperature and normal pressure, uniform air intake or temperature reduction and pressure reduction relative to the whole machine, so that the differences between the inlet pressure, temperature, flow field, constant-pressure specific heat, specific heat ratio, clearance and the like of the component and the environment of the whole machine are large, the characteristics of the component and the real performance of the component on the whole machine are greatly different, and the actual performance of each component cannot be effectively evaluated.
At present, the main way for mastering the matching working condition among all the parts is a complete machine full-flow test, but in the view of the whole machine full-flow test result in the past, due to the limitations of test equipment and a measurement method, the characteristics of a fan, the characteristics of a gas compressor, the reduced flow of a high-pressure turbine and the total pressure recovery coefficient of a combustion chamber cannot be obtained under the condition of the complete machine, and the performance accuracy of the obtained parts such as the expansion ratio of the high-pressure turbine is not high, so that the working states of the parts such as the fan, the gas compressor, the high-pressure turbine and the low-pressure turbine are difficult to accurately evaluate, and meanwhile, greater uncertain factors are brought to the.
Disclosure of Invention
In order to solve the above problems, the present application provides a method for obtaining actual performance of each component of an engine under a complete machine condition, which mainly comprises:
a fan characteristic determining step: changing the working point of the fan by adjusting the area of the outlet of the external culvert to obtain the characteristics of the fan under the condition of the whole machine;
compressor characteristic determination: heating and pressurizing at an inlet of a core machine, performing flow field disturbance to simulate the working environment of the compressor under the condition of the whole machine, and performing angle adjustment tests of fixed spray pipes and adjustable guide vanes of the compressor with different areas to obtain the characteristics of the compressor under the condition of simulating the environment of the whole machine, wherein the core machine is an engine structure consisting of the compressor, a combustion chamber and a high-pressure turbine;
determining the performance of a main combustion chamber and an afterburner chamber: under the condition of the whole machine, the total pressure recovery coefficient of the main combustion chamber is calculated by adopting static pressure loss instead of total pressure loss, and the combustion efficiency of the main combustion chamber and the afterburner is obtained by analyzing the components of gas;
a turbine performance determining step: firstly, measuring the total pressure at the outlet of a high-pressure turbine to obtain a high turbine expansion ratio, and then obtaining a low-pressure turbine expansion ratio according to the total expansion ratio of each rotating speed state and the pressure at the outlet of a culvert;
air system bleed air quantity determining step: the engine turbine cooling air sealing structure, the pipeline and the nozzle are extracted from the whole machine part, the flow characteristics of the engine turbine cooling air sealing structure, the pipeline and the nozzle are obtained through tests, the positions of measuring points which are measured for multiple times in each cavity are solidified according to the simulation calculation results of each cavity of the engine turbine, and further the air entraining amount of each flow path is determined.
Preferably, in the fan characteristic determining step, the bypass outlet area is adjusted by providing a throttle valve at the engine bypass outlet.
Preferably, in the fan characteristic determining step, the fan characteristics include a fan flow rate, a fan pressure ratio, a fan efficiency, and a fan surge margin.
Preferably, in the compressor characteristic determining step, the compressor characteristics include a compressor converted flow rate, a compressor pressure ratio, a compressor efficiency, and a compressor surge margin.
Preferably, in the compressor characteristic determining step, the flow field disturbance at the inlet of the core engine includes:
and a spoiler network for simulating the flow field of the fan outlet of the whole machine is arranged at the inlet of the core machine.
Preferably, in the air system bleed air amount determination step, the test lead is fixed by machining a fixing seat.
In order to effectively evaluate the actual performance of each part, the application provides a method for evaluating the actual performance of each part of the engine under the condition of a complete machine of 'one set of hardware and distributed implementation':
a set of hardware: the states of the engine components are consistent in the whole staged test process, all hardware cannot be replaced in the middle, and the consistency performance and effectiveness of test results are guaranteed.
Distribution implementation: the actual performance evaluation test of each part under the condition of the whole machine is divided into 2 parts and 5 stages; 2 parts are a core machine test part and a whole machine test part; the 5 stages are a fan characteristic recording test, a gas compressor characteristic recording test, a main combustion and stress application performance recording test, a high-pressure and low-pressure turbine performance recording test and an air entraining amount determining test of an air system.
The method and the device solve the problem that performance and matching working condition of each part are not accurately evaluated in the actual working environment of the whole machine. The method and the device can obtain the actual performance and the mutual matching relation of all the parts in the working environment of the whole machine, and can provide important support for the matching optimization of the whole machine, the evaluation of the strength and the service life, the improvement of the parts and the evaluation of the pneumatic stability.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of a method for obtaining actual performance of engine components under overall conditions of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The first aspect of the present application provides a method for obtaining actual performance of each component of an engine under a complete machine condition, as shown in fig. 1, the method mainly includes:
a fan characteristic determining step: changing the working point of the fan by adjusting the area of the outlet of the external culvert to obtain the characteristics of the fan under the condition of the whole machine;
compressor characteristic determination: heating and pressurizing at an inlet of a core machine, performing flow field disturbance to simulate the working environment of the compressor under the condition of the whole machine, and performing angle adjustment tests of fixed spray pipes and adjustable guide vanes of the compressor with different areas to obtain the characteristics of the compressor under the condition of simulating the environment of the whole machine, wherein the core machine is an engine structure consisting of the compressor, a combustion chamber and a high-pressure turbine;
determining the performance of a main combustion chamber and an afterburner chamber: under the condition of the whole machine, the total pressure recovery coefficient of the main combustion chamber is calculated by adopting static pressure loss instead of total pressure loss, and the combustion efficiency of the main combustion chamber and the afterburner is obtained by analyzing the components of gas;
a turbine performance determining step: firstly, measuring the total pressure at the outlet of a high-pressure turbine to obtain a high turbine expansion ratio, and then obtaining a low-pressure turbine expansion ratio according to the total expansion ratio of each rotating speed state and the pressure at the outlet of a culvert;
air system bleed air quantity determining step: the engine turbine cooling air sealing structure, the pipeline and the nozzle are extracted from the whole machine part, the flow characteristics of the engine turbine cooling air sealing structure, the pipeline and the nozzle are obtained through tests, the positions of measuring points which are measured for multiple times in each cavity are solidified according to the simulation calculation results of each cavity of the engine turbine, and further the air entraining amount of each flow path is determined.
The details will be described below.
1. Fan characteristic determination
In order to obtain the fan characteristics under the complete machine condition, a process spray pipe is adopted, and the area A16 of a bypass outlet is reduced through a throttle valve on the process spray pipe to improve the working point of the fan, so that the fan characteristics under the complete machine condition are obtained. The method requires the manufacture of a process nozzle with a throttle valve.
The total temperature, total pressure and static pressure of the fan inlet and the total temperature and total pressure of the fan outlet are measured in the test process, the working point of the fan is changed by adjusting the bypass area A16 through adjusting a throttle valve on a process spray pipe at a specified rotating speed, and the inlet and outlet parameters of the fan from the blocking point to the surge point at the rotating speed are obtained, so that the rotating speed characteristics of the fan under the condition of the whole machine, including the flow rate, the pressure ratio, the efficiency and the surge margin of the fan, are obtained.
2. Compressor characterization
Due to the structural characteristics of the intermediate casing, the inlet flow and the characteristics of the compressor cannot be directly measured under the condition of the whole machine at present. In order to obtain accurate characteristics of the compressor, the embodiment of the application provides a method for simulating the working environment of the compressor under the complete machine condition by using a core machine, namely, a spoiler network for simulating the flow field of an outlet of a fan of the complete machine is arranged at an inlet of the core machine, the working environment of the compressor under the complete machine condition is simulated by heating and pressurizing the inlet of the core machine, and on the basis, fixed spray pipes with different areas and the angle a of an adjustable guide vane of the compressor are developed2And adjusting the test to obtain the actual performance of the gas compressor under the condition of simulating the whole machine environment, wherein the actual performance comprises the converted flow, the pressure ratio, the efficiency and the surge margin of the gas compressor.
3. Main and boost performance determination
The main combustion chamber has high working temperature under the condition of the whole machine, and no inductive part capable of measuring the total pressure of the outlet of the main combustion chamber exists at present, so that the total pressure recovery coefficient of the main combustion chamber cannot be obtained under the condition of the whole machine. In order to obtain the total pressure recovery coefficient of the main combustion chamber, a method for replacing the total pressure loss by the static pressure loss is provided in one embodiment of the application. The method effectively avoids the risk that the sensed part directly permeates into a high-temperature flow field, and solves the problem that the total pressure sensed part is arranged in narrow spaces such as a flame tube.
In order to obtain the combustion efficiency of the main combustion chamber and the afterburner, in an embodiment of the application, a gas analyzer is adopted to measure the gas components, and the combustion efficiency of the main combustion chamber and the afterburner is obtained by analyzing the gas components.
4. High and low pressure turbine performance determination
The high-pressure turbine outlet temperature of the advanced engine is high, and a pressure sensing part which can bear the high temperature without cooling does not exist at present, so that the high-pressure turbine expansion ratio cannot be accurately estimated. In order to determine the performance evaluation requirements of the high-pressure turbine and the low-pressure turbine, in an embodiment of the application, a method for replacing the expansion ratio of the high-speed state with the expansion ratio of the low-speed state after the throat of the high-pressure turbine guider is critical is provided, namely, a pressure sensing part capable of bearing the temperature after the high-pressure turbine guider is critical is machined, the total pressure of an outlet of the high-pressure turbine is directly measured, the expansion ratio of the high-pressure turbine is obtained, and then the expansion ratio of the low-pressure turbine is obtained according to the total expansion ratio of each speed state and the.
5. Air system bleed air quantity determination
The advanced engine has high turbine temperature, a large amount of used cooling air, complex flow path, and various sealing structures, pipelines and cavity resistance influence the flow of the cooling air, so that the working state of the engine deviates from the design state. From the measurement results of the air system of the complete machine in the previous period, the measurement results of the air system are large in dispersion degree, the measurement accuracy is not high, and the air entraining amount of each flow path cannot be accurately determined. In order to solve the problems, in the embodiment of the application, the sealing structure, the pipeline, the nozzle and the like which influence the measurement dispersion degree are extracted from the whole engine, special blowing and measurement tests are performed, and the flow characteristics of the sealing structure, the pipeline and the like are obtained. Meanwhile, aiming at the problem that the positions of the measuring points are not repeated every time, a measuring point fixing method based on three-dimensional simulation is provided, namely, the positions of the measuring points in each cavity are determined according to the simulation calculation result of each cavity, and a test lead is fixed by adopting a fixing seat. The method effectively solves the problems of large dispersion degree of the measuring points and low measuring accuracy.
The key points and the protection points of the application are mainly as follows:
1) test method
In order to obtain the actual performance of each part under the condition of the whole machine, a test method of 'one set of hardware and distributed implementation' is provided. A set of hardware: the states of the engine components are consistent in the whole staged test process, all hardware cannot be replaced in the middle, and the consistency performance and effectiveness of test results are guaranteed. Distribution implementation: the actual performance evaluation test of each part under the condition of the whole machine is divided into 2 parts and 5 stages; 2 parts are a core machine test part and a whole machine test part; the 5 stages are a fan characteristic recording test, a gas compressor characteristic recording test, a main combustion and stress application performance recording test, a high-pressure and low-pressure turbine performance recording test and an air entraining amount determining test of an air system.
2) Method for evaluating actual performance of each component
In order to obtain the characteristics of the fan under the condition of the whole machine, a method for adjusting the area A16 of an outlet of a culvert and the working point of the fan by using a process spray pipe is adopted; in order to obtain the total pressure recovery coefficients of the main combustion chamber and the afterburner, a method of replacing total pressure loss by static pressure loss is adopted, so that the problem that the sensed part directly permeates into a high-temperature flow field is effectively avoided; in order to obtain the performances of the high-pressure turbine and the low-pressure turbine, a pressure sensing part is adopted to directly measure the total pressure behind the high-pressure turbine, and the performances such as the expansion ratio of the high-pressure turbine and the low-pressure turbine are obtained.
3) Test instrument and test layout
Aiming at the problem that influences of boundary layers, blade outlet trails and the like on evaluation accuracy cannot be considered in the previous part performance evaluation test, a plurality of meters are adopted. The penetrating rakes adopted on the air inlet channels of the core machine and the whole machine can consider the influence of boundary layers in the air inlet channels; the arc-shaped harrow adopted at the outlets of the fan, the gas compressor and the low-pressure turbine can measure the wake of the outlet of the blade under the condition of the whole machine, thereby effectively improving the performance evaluation precision of the fan, the gas compressor and the low-pressure turbine.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A method for obtaining actual performance of each part of an engine under the condition of a complete machine is characterized by comprising the following steps:
a fan characteristic determining step: changing the working point of the fan by adjusting the area of the outlet of the external culvert to obtain the characteristics of the fan under the condition of the whole machine;
compressor characteristic determination: heating and pressurizing at an inlet of a core machine, performing flow field disturbance to simulate the working environment of the compressor under the condition of the whole machine, and performing angle adjustment tests of fixed spray pipes and adjustable guide vanes of the compressor with different areas to obtain the characteristics of the compressor under the condition of simulating the environment of the whole machine, wherein the core machine is an engine structure consisting of the compressor, a combustion chamber and a high-pressure turbine;
determining the performance of a main combustion chamber and an afterburner chamber: under the condition of the whole machine, the total pressure recovery coefficient of the main combustion chamber is calculated by adopting static pressure loss instead of total pressure loss, and the combustion efficiency of the main combustion chamber and the afterburner is obtained by analyzing the components of gas;
a turbine performance determining step: firstly, measuring the total pressure at the outlet of a high-pressure turbine to obtain a high turbine expansion ratio, and then obtaining a low-pressure turbine expansion ratio according to the total expansion ratio of each rotating speed state and the pressure at the outlet of a culvert;
air system bleed air quantity determining step: the engine turbine cooling air sealing structure, the pipeline and the nozzle are extracted from the whole machine part, the flow characteristics of the engine turbine cooling air sealing structure, the pipeline and the nozzle are obtained through tests, the positions of measuring points which are measured for multiple times in each cavity are solidified according to the simulation calculation results of each cavity of the engine turbine, and further the air entraining amount of each flow path is determined.
2. The method for obtaining the actual performance of each component of the engine under the complete machine condition as set forth in claim 1, wherein in the fan characteristic determining step, the area of the bypass outlet is adjusted by providing a throttle valve at the bypass outlet of the engine.
3. The method for obtaining actual performance of each component of an engine under overall conditions of claim 1, wherein in the fan characteristic determining step, the fan characteristics include fan flow, fan pressure ratio, fan efficiency, and fan surge margin.
4. The method for obtaining the actual performance of each component of the engine under the complete machine condition as claimed in claim 1, wherein in the compressor characteristic determining step, the compressor characteristics include a compressor converted flow rate, a compressor pressure ratio, a compressor efficiency and a compressor surge margin.
5. The method for obtaining actual performance of each component of an engine under complete machine conditions as claimed in claim 1, wherein the compressor characteristic determining step, performing flow field disturbance at the inlet of the core machine comprises:
and a spoiler network for simulating the flow field of the fan outlet of the whole machine is arranged at the inlet of the core machine.
6. The method for obtaining the actual performance of each part of the engine under the complete machine condition as claimed in claim 1, wherein in the air system bleed air quantity determining step, the test lead is fixed by processing a fixed seat.
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| CN113221294A (en) * | 2021-06-18 | 2021-08-06 | 中国航发沈阳发动机研究所 | Method for obtaining expansion ratio of high-low pressure turbine under complete engine condition |
| CN113361040A (en) * | 2021-06-18 | 2021-09-07 | 中国航发沈阳发动机研究所 | Method for evaluating outlet temperature of combustion chamber under engine complete machine condition |
| CN113449475A (en) * | 2021-06-23 | 2021-09-28 | 中国航发沈阳发动机研究所 | Method for predicting inlet pressure distortion intensity of gas turbine engine |
| CN113702058A (en) * | 2021-09-16 | 2021-11-26 | 成立航空股份有限公司 | Combustion test method for pressure reduction simulation of combustion chamber of gas turbine |
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