CN108197342B - Method for calculating non-design air leakage of air system of aircraft engine - Google Patents
Method for calculating non-design air leakage of air system of aircraft engine Download PDFInfo
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Abstract
The invention relates to the field of design of air systems of aero-engines, in particular to a method for calculating non-design air leakage of an air system of an aero-engine. The calculation method comprises the following steps: dividing the flow path into an upstream typical flow structure, a complex blow-by structure, and a downstream typical flow structure; carrying out unit-level flow characteristic tests aiming at the upstream typical flow structure and the downstream typical flow structure respectively to obtain the corresponding relation between the flow of the upstream typical flow structure and the downstream typical flow structure and the inlet-outlet pressure ratio; respectively carrying out inlet and outlet pressure measurement of the upstream and downstream typical flow structures to obtain inlet and outlet pressures of the upstream and downstream typical flow structures; respectively calculating the upstream and downstream typical flow structure flow; calculating the non-design air leakage of the complex air leakage structure; the method for calculating the non-design air leakage of the air system of the aero-engine can accurately obtain the non-design air leakage of a complex structure, greatly improve the design precision of the air system of the aero-engine, realize the function of the air system and ensure the operation safety of the aero-engine.
Description
Technical Field
The invention relates to the field of design of air systems of aero-engines, in particular to a method for calculating non-design air leakage of an air system of an aero-engine.
Background
The air system of the aircraft engine is formed by introducing air by a high-pressure compressor, and the air flows to an engine disc cavity through a pipeline, a gas collection cavity, a vent hole, a labyrinth and other structures, so that the functions of disc shaft temperature equalization/cooling, rotor axial force adjustment, disc edge sealing and the like are realized. The flow path structure of the air system in the engine design adopts a corresponding sealing form, and is considered according to complete sealing, but the complete sealing and leakage, namely non-design air leakage, can not be realized due to the influence of processing, assembly and thermal working environment. If the air system flow path has non-design air leakage, the pressure of a downstream cavity of the flow path is insufficient, the amount of cold air is reduced and the like, so that the air system deviates from the design target, related functions cannot be realized, and the operation safety of an aircraft engine is seriously influenced, so that the analysis of the non-design air leakage of the air system flow path of the aircraft engine is particularly important.
The aeroengine air system flow path has complex structure along the way, the structure form of the air leakage position is various, and the analysis difficulty is increased because the air leakage structure is influenced by the thermal working environment.
In the past, for non-design air leakage of a complex structure along the path of an air system flow path of an aircraft engine, the area of the non-design air leakage is estimated generally according to experience, a non-design air leakage unit is modeled in an air system network, and the non-design air leakage amount is calculated; however, in the method, the estimation of the non-design leakage area is based on design experience, the leakage position is usually a complex atypical unit structure, and deviation exists in unit modeling calculation, so that the method has a large error, which may cause the air system to deviate from a design target, related functions cannot be realized, and the operation safety of the aircraft engine is influenced.
In addition, if the non-design air leakage of the complex structure cannot be accurately analyzed in the design stage, the function of the air system cannot be realized. In the process of engine test run, relevant faults occur, field solutions are not provided, and only the engine can be disassembled and redesigned on the next stage, so that the test period is greatly prolonged, and the economic cost and the time cost are obviously increased.
Disclosure of Invention
The invention aims to provide a method for calculating the non-design air leakage of an air system of an aircraft engine, which is used for solving at least one problem of the existing method for calculating the non-design air leakage of the air system of the aircraft engine.
The technical scheme of the invention is as follows:
a method for calculating the non-design leakage of an air system of an aircraft engine comprises the following steps:
dividing a flow path of an air system of an aircraft engine into three unit-level modules of an upstream typical flow structure, a complex air leakage structure and a downstream typical flow structure;
step two, carrying out unit-level flow characteristic tests aiming at an upstream typical flow structure and a downstream typical flow structure respectively, and obtaining the corresponding relation between the flow of the upstream typical flow structure and the downstream typical flow structure and the pressure ratio of an inlet and an outlet respectively;
thirdly, respectively carrying out inlet and outlet pressure measurement of an upstream typical flow structure and a downstream typical flow structure on a flow path of an air system of the aircraft engine to obtain inlet and outlet pressures of the upstream typical flow structure and the downstream typical flow structure;
step four, respectively calculating the flow of the upstream typical flow structure and the flow of the downstream typical flow structure according to the corresponding relation between the flow obtained in the step two and the inlet-outlet pressure ratio and the inlet-outlet pressure obtained in the step three;
and step five, calculating the non-design air leakage of the complex air leakage structure.
Optionally, the method for calculating the non-design leakage of the air system of the aircraft engine further includes:
and step six, respectively carrying out the tests of the step three to the step five under different thermal state working environments on an air system of the aeroengine to obtain the non-design air leakage of the complex structure under different thermal state working environments.
Optionally, in the second step, performing a unit-level flow characteristic test on the upstream typical flow structure includes:
2.11, measuring the flow of the upstream typical structure by using a flow meter;
2.12, measuring the pressure of the inlet and the outlet in corresponding states by using a pressure sensor;
step 2.13, obtaining the corresponding relation between the upstream typical structure flow and the inlet-outlet pressure ratio;
conducting unit-level flow characterization tests on an upstream representative flow structure includes:
2.21, measuring the flow of the downstream typical structure by using a flow meter;
2.22, measuring the pressure of the inlet and the outlet in corresponding states by using a pressure sensor;
and 2.23, obtaining the corresponding relation between the flow of the downstream typical structure and the inlet-outlet pressure ratio.
Optionally, in the third step, the upstream typical flow structure inlet-outlet pressure measurement includes:
arranging pressure measuring points at an inlet and an outlet of the upstream typical flow structure to obtain inlet and outlet pressures of the upstream typical flow structure;
and arranging pressure measuring points at the inlet and the outlet of the downstream typical flow structure to obtain the inlet and outlet pressures of the downstream typical flow structure.
Optionally, in the fifth step, the air leakage of the complex air leakage structure is calculated according to the fact that the air leakage is equal to the difference between the inlet flow and the outlet flow
The invention has the following effects:
the method for calculating the non-design air leakage of the air system of the aero-engine can accurately obtain the non-design air leakage of a complex structure, greatly improve the design precision of the air system of the aero-engine, realize the function of the air system and ensure the operation safety of the aero-engine.
Drawings
FIG. 1 is a schematic flow diagram of a method for calculating the non-design leakage of an aircraft engine air system according to the present invention.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. 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 only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
The method for calculating the non-design leakage of the air system of the aircraft engine is further described in detail with reference to the attached drawing 1.
The invention provides a method for calculating non-design air leakage of an air system of an aircraft engine, which comprises the following steps:
step one, analyzing the characteristics of a flow path according to needs, and dividing the flow path of an air system of the aircraft engine into three unit-level modules, namely an upstream typical flow structure, a complex air leakage structure and a downstream typical flow structure.
And step two, carrying out unit-level flow characteristic tests aiming at the upstream typical flow structure and the downstream typical flow structure respectively, and obtaining the corresponding relation between the flow of the upstream typical flow structure and the downstream typical flow structure and the inlet-outlet pressure ratio respectively.
Specifically, conducting unit-level flow characteristic tests on upstream representative flow structures includes:
step 2.11, flow meter is used for measuring flow G of upstream typical structures；
Step 2.12, measuring the pressure P of the inlet in the corresponding state by using the pressure sensorinPressure P at the outletout；
Step 2.13, obtaining the corresponding relation between the upstream typical structure flow and the inlet-outlet pressure ratio:
wherein ξsIs the flow coefficient;
conducting unit-level flow characterization tests on an upstream representative flow structure includes:
step 2.21, flow meter is used for measuring flow G of downstream typical structurex；
Step 2.22, measuring the pressure P of the inlet in the corresponding state by using the pressure sensorinPressure P at the outletout；
Step 2.23, obtaining the corresponding relation between the flow of the downstream typical structure and the pressure ratio of the inlet and the outlet:
wherein ξxIs the flow coefficient;
and thirdly, respectively carrying out inlet and outlet pressure measurement on the upstream typical flow structure and the downstream typical flow structure on a flow path of an air system of the aircraft engine to obtain inlet and outlet pressures of the upstream typical flow structure and the downstream typical flow structure.
Specifically, pressure measuring points and inlet pressure measuring points are arranged at the inlet and the outlet of the upstream typical flow structure
Outlet pressure measurement point
Obtaining inlet and outlet pressures of an upstream representative structure;
pressure measuring points and inlet pressure measuring points are arranged at the inlet and the outlet of the downstream typical flow structure
Outlet pressure measurement point
Inlet and outlet pressures for the downstream representative structures are obtained.
And step four, respectively calculating the flow of the upstream typical flow structure and the flow of the downstream typical flow structure according to the corresponding relation between the flow obtained in the step two and the inlet-outlet pressure ratio and the inlet-outlet pressure obtained in the step three.
Specifically, the corresponding relation between the upstream typical structure flow and the inlet-outlet pressure ratio obtained according to the zero unit level flow characteristic test is as follows:
and obtained by testing the flow path of the system
And
calculating and obtaining the typical structure flow G at the upstream of the test state in the system flow paths；
The corresponding relation between the downstream typical structure flow and the inlet-outlet pressure ratio is obtained according to the unit-level flow characteristic test:
and obtained by testing the flow path of the system
And
calculating and obtaining the flow G of the typical structure at the downstream of the test state in the system flow pathx。
And step five, calculating the non-design air leakage of the complex air leakage structure.
Specifically, the air leakage is based on inlet flow-outlet flow, i.e. Gr＝GS-GXAnd calculating the non-design air leakage of the complex air leakage structure.
Further, the method for calculating the non-design leakage of the air system of the aircraft engine further comprises the following steps:
and step six, respectively carrying out the tests of the step three to the step five under different thermal state working environments on an air system of the aeroengine to obtain the non-design air leakage of the complex structure under different thermal state working environments.
In the analysis method, the flow of the upstream and downstream typical flow structures is obtained through the flow characteristics and the inlet and outlet pressure test measurement results, and the air leakage of the complex air leakage structure is obtained on the basis.
The method for calculating the non-design air leakage of the air system of the aero-engine can accurately obtain the non-design air leakage of a complex structure, greatly improve the design precision of the air system of the aero-engine, realize the function of the air system and ensure the operation safety of the aero-engine; in addition, the method can be used for the non-design air leakage analysis of the complex structure under different thermal state working environments, so that the method is suitable for the aircraft engines under different working states.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention 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 invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (3)
1. A method for calculating the non-design leakage of an air system of an aircraft engine is characterized by comprising the following steps:
dividing a flow path of an air system of an aircraft engine into three unit-level modules of an upstream typical flow structure, a complex air leakage structure and a downstream typical flow structure;
step two, carrying out unit-level flow characteristic tests aiming at an upstream typical flow structure and a downstream typical flow structure respectively, and obtaining the corresponding relation between the flow of the upstream typical flow structure and the downstream typical flow structure and the pressure ratio of an inlet and an outlet respectively;
conducting unit-level flow characterization tests on an upstream representative flow structure includes:
2.11, measuring the flow of the upstream typical structure by using a flow meter;
2.12, measuring the pressure of the inlet and the outlet in corresponding states by using a pressure sensor;
step 2.13, obtaining the corresponding relation between the upstream typical structure flow and the inlet-outlet pressure ratio;
wherein G issIs the flow of the upstream typical structure, PinPressure at the inlet of the upstream typical structure, PoutPressure, ξ, at the outlet of the upstream exemplary structuresIs the flow coefficient;
conducting unit-level flow characterization tests on a downstream representative flow structure includes:
2.21, measuring the flow of the downstream typical structure by using a flow meter;
2.22, measuring the pressure of the inlet and the outlet in corresponding states by using a pressure sensor;
step 2.23, obtaining the corresponding relation between the flow of the downstream typical structure and the pressure ratio of the inlet and the outlet;
wherein G isxIs the flow of the downstream typical structure, PinPressure at the inlet of the downstream typical structure, PoutPressure, ξ, at the outlet of a typical downstream structurexIs the flow coefficient;
thirdly, respectively carrying out inlet and outlet pressure measurement of an upstream typical flow structure and a downstream typical flow structure on a flow path of an air system of the aircraft engine to obtain inlet and outlet pressures of the upstream typical flow structure and the downstream typical flow structure;
step four, respectively calculating the flow of the upstream typical flow structure and the flow of the downstream typical flow structure according to the corresponding relation between the flow obtained in the step two and the inlet-outlet pressure ratio and the inlet-outlet pressure obtained in the step three;
calculating the non-design air leakage of the complex air leakage structure;
and step six, respectively carrying out the tests of the step three to the step five under different thermal state working environments on an air system of the aeroengine to obtain the non-design air leakage of the complex structure under different thermal state working environments.
2. The aircraft engine air system non-design leak calculation method according to claim 1, wherein in step three, the upstream typical flow structure inlet-outlet pressure measurement comprises:
arranging pressure measuring points at an inlet and an outlet of the upstream typical flow structure to obtain inlet and outlet pressures of the upstream typical flow structure;
and arranging pressure measuring points at the inlet and the outlet of the downstream typical flow structure to obtain the inlet and outlet pressures of the downstream typical flow structure.
3. The aircraft engine air system off-design leakage calculation method according to claim 1, wherein in step five, the leakage of the complex leakage structure is calculated based on the leakage being equal to the difference between the inlet flow and the outlet flow.
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| CN113899557B (en) * | 2020-06-22 | 2023-11-28 | 中国航发商用航空发动机有限责任公司 | Method and device for determining characteristics of an aeroengine air system |
| CN115795705B (en) * | 2022-10-19 | 2024-01-02 | 中国航发沈阳发动机研究所 | Air entraining pipeline of air system of aero-engine and design method of flow resistance characteristics of air entraining pipeline |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202008013127U1 (en) * | 2008-10-01 | 2009-11-12 | Boge & Co. Maschinenhandelsgesellschaft Gmbh & Co. Kg | Device for detecting leakage of a compressed air system |
| CN102607658A (en) * | 2012-03-08 | 2012-07-25 | 北京航空航天大学 | Method for measuring gas flow in complicated structure channel based on concentration method |
| CN103366078A (en) * | 2012-04-05 | 2013-10-23 | 中国航空工业集团公司沈阳发动机设计研究所 | Bearing cavity ventilation design method of aero-engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB2132367B (en) * | 1982-11-10 | 1986-01-15 | Rolls Royce | Thrust and airflow monitor for aeroengine test cells |
| CN102269030A (en) * | 2011-06-23 | 2011-12-07 | 潍柴动力股份有限公司 | Oil-gas separator and crankcase blow-by amount detection control system with same |
| CN105117561B (en) * | 2015-09-16 | 2019-10-22 | 中国航空工业集团公司沈阳发动机设计研究所 | Contain design method outside a kind of aero-engine |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202008013127U1 (en) * | 2008-10-01 | 2009-11-12 | Boge & Co. Maschinenhandelsgesellschaft Gmbh & Co. Kg | Device for detecting leakage of a compressed air system |
| CN102607658A (en) * | 2012-03-08 | 2012-07-25 | 北京航空航天大学 | Method for measuring gas flow in complicated structure channel based on concentration method |
| CN103366078A (en) * | 2012-04-05 | 2013-10-23 | 中国航空工业集团公司沈阳发动机设计研究所 | Bearing cavity ventilation design method of aero-engine |
Non-Patent Citations (2)
| Title |
|---|
| 《航空发动机性能与二次空气***的耦合仿真模型》;刘传凯等;《航空动力学报》;20170731;第1623-1630页 * |
| 《航空发动机空气流量测量与计算方法研究》;史建邦等;《工程与试验》;20111231;第15-18,41页 * |
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