CN113899559B - Reconstruction method and device for air inlet total temperature fault of aero-engine - Google Patents
Reconstruction method and device for air inlet total temperature fault of aero-engine Download PDFInfo
- Publication number
- CN113899559B CN113899559B CN202111394455.2A CN202111394455A CN113899559B CN 113899559 B CN113899559 B CN 113899559B CN 202111394455 A CN202111394455 A CN 202111394455A CN 113899559 B CN113899559 B CN 113899559B
- Authority
- CN
- China
- Prior art keywords
- total
- pressure
- outlet
- temperature
- fan
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
- G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
- G01K13/024—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow of moving gases
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
- G06F17/15—Correlation function computation including computation of convolution operations
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Mathematical Physics (AREA)
- Computational Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Data Mining & Analysis (AREA)
- Algebra (AREA)
- Databases & Information Systems (AREA)
- Software Systems (AREA)
- General Engineering & Computer Science (AREA)
- Computing Systems (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The application belongs to the field of engine fault detection and treatment, and particularly relates to a reconstruction method and device for an aeroengine air inlet total temperature fault, wherein the method comprises the following steps: step S1: acquiring the total inlet pressure of a fan of a turbofan engine, and the total outlet temperature and the total outlet pressure of a compressor; step S2: fitting a variable compression efficiency based on an inlet total pressure of the turbofan engine fan and an outlet total pressure of the compressor; step S3: based on the variable compression efficiency, the total inlet pressure of the turbofan engine fan, the total outlet temperature of the air compressor and the total outlet pressure, an air inlet total temperature reconstruction model of the turbofan engine fan is built.
Description
Technical Field
The application belongs to the field of engine fault detection and treatment, and particularly relates to a reconstruction method device for an air inlet total temperature fault under a full-envelope complex working condition of an aeroengine.
Background
The new generation advanced small bypass ratio turbofan engine control system adopts a dual-redundancy full-right digital electronic control mode, and because no mechanical hydraulic backup exists, higher requirements are put forward on fault diagnosis and treatment countermeasures, wherein the total air inlet temperature of the fan is used as the main control parameter of the engine, if a fan total air inlet temperature sensor breaks down, a model needs to be built to calculate and reconstruct the total air inlet temperature of the fan, and the calculated total air inlet temperature needs to ensure that the engine can safely work within a certain range.
The existing method for reconstructing the total temperature of the air inlet adopts parameters such as the altitude, mach number and the like transmitted to an engine by an airplane to reconstruct, firstly solves the static temperature by the altitude, and then solves the total temperature according to the Mach number.
Disclosure of Invention
In order to solve the above problems, a first aspect of the present application provides a reconstruction method for an aero-engine intake total temperature fault, including the following steps:
step S1: acquiring the total inlet pressure of a fan of a turbofan engine, and the total outlet temperature and the total outlet pressure of a compressor;
step S2: fitting a variable compression efficiency based on an inlet total pressure of the turbofan engine fan and an outlet total pressure of the compressor;
step S3: and establishing an air inlet total temperature reconstruction model of the turbofan engine fan based on the variable compression efficiency, the inlet total pressure of the turbofan engine fan, the outlet total temperature of the compressor and the outlet total pressure.
Preferably, the polytropic compression efficiency is obtained by a function of a high altitude bench test data fit.
Preferably, the function comprises a 2-degree function.
Preferably, in the step S3, an intake total temperature reconstruction model of the turbofan engine fan is established based on the variable compression efficiency, the total inlet pressure of the turbofan engine fan, the total outlet temperature of the compressor and the total outlet pressure, and the specific model is as follows:
wherein:T t2 the total temperature of the air inlet of the fan is used,T t3 is the total temperature of the outlet of the air compressor,P t2 is the total pressure of the inlet of the fan,P t3 Is the total pressure of the outlet of the air compressor, k is the specific heat ratio, E c Is a variable compression efficiency.
Preferably, k takes a value of 1.4.
Preferably, the high-altitude table test data is obtained by removing outliers.
Preferably, the function comprises an equality relation function of the polytropic compression efficiency, the total pressure of the inlet of the turbofan engine fan and the total pressure of the outlet of the compressor.
Preferably, the total pressure of the inlet of the turbofan engine fan and the total pressure of the outlet of the compressor are in a ratio relationship in the equality relationship function.
The second aspect of the present application provides a reconstruction device corresponding to the above method when the total air intake temperature of the aero-engine fails, mainly including:
the total pressure acquisition module is used for acquiring the total inlet pressure of the fan of the turbofan engine, and the total outlet temperature and the total outlet pressure of the air compressor;
the fitting module is used for fitting the variable compression efficiency based on the total inlet pressure of the turbofan engine fan and the total outlet pressure of the compressor;
and the reconstruction module is used for establishing an air inlet total temperature reconstruction model of the turbofan engine fan based on the variable compression efficiency, the inlet total pressure of the turbofan engine fan, the outlet total temperature of the air compressor and the outlet total pressure.
Preferably, the reconstruction module relates to a reconstruction model as follows:
wherein:T t2 the total temperature of the air inlet of the fan is used,T t3 is the total temperature of the outlet of the air compressor,P t2 is the total pressure of the inlet of the fan,P t3 Is the total pressure of the outlet of the air compressor, k is the specific heat ratio, E c Is of variable compression efficiency。
The advantages of the present application include: according to the invention, the total air intake temperature parameter is calculated and reconstructed through the engine measurement parameters, so that the accurate reconstruction of the total air intake temperature under the complex working condition of the whole envelope of the aero-engine is realized, the problem that the aero-engine controlled by the full-authority digital electronic control is not accurately controlled when the total air intake temperature fails is solved, the parameters such as the altitude H, ma input by an airplane are not needed during parameter reconstruction, the reconstruction closed loop of the engine self-parameters is realized, the dependence on the parameters of the airplane is eliminated, the reliability of the reconstruction of the engine self-parameters is improved, and the method has great significance for the fault diagnosis and treatment countermeasure formulation of an engine fault control system.
Drawings
FIG. 1 is a schematic cross-sectional view of a turbofan engine;
FIG. 2 is a graph of polytropic compression efficiency versus Pt 3/Pt 2.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the following describes the technical solutions in the embodiments of the present application in more detail with reference to the 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, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, based on the embodiments herein, which would be apparent to one of ordinary skill in the art without undue burden are within the scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The first aspect of the application provides a reconstruction method for an aeroengine air inlet total temperature fault, which comprises the following steps:
step S1: obtaining the total inlet pressure of a fan of a turbofan engine, and the total outlet temperature and the total outlet pressure of a gas compressor, wherein as shown in fig. 1, for the turbofan engine, when the engine characteristics are approximately calculated, the fan and the gas compressor are regarded as a whole, and the fan is connected with the gas compressor;
step S2: fitting a variable compression efficiency based on an inlet total pressure of the turbofan engine fan and an outlet total pressure of the compressor; wherein the variable compression efficiency is E c Can be obtained by fitting test data of a high altitude platform, and E is obtained by analysis c The function relation mainly related to Pt 3/Pt 2 is generally fitted to a 2-degree function, and taking a certain engine as an example, the fitted function is obtained as follows:
the curve is shown in fig. 2.
Step S3: based on the variable compression efficiency, the total inlet pressure of the turbofan engine fan, the total outlet temperature of the compressor and the total outlet pressure, an inlet total temperature reconstruction model of the turbofan engine fan is established, and the model specifically comprises the following steps: wherein the section 2 is a fan inlet, the section 3 is a high-pressure compressor outlet, the total temperature and the total pressure of the inlet and the outlet can be obtained by measurement, and whenT t2 In case of a measurement failure, the method can be used forT t3 、P t2 、P t3 The method for calculating the reconstruction is as follows:
substituting the fitted variable compression efficiency into the like to obtain a final reconstruction model:
wherein, the liquid crystal display device comprises a liquid crystal display device,T t2 the total temperature of the air inlet of the fan is used,T t3 is the outlet assembly of the air compressorThe temperature of the mixture is high, the temperature of the mixture is low,P t2 is the total pressure of the inlet of the fan,P t3 Is the total pressure of the outlet of the air compressor, k is the specific heat ratio, E c Is a variable compression efficiency.
When k is 1.4, the following is obtained:
when the parameters are reconstructed, parameters such as the altitude H, ma input by an airplane are not needed, the reconstruction closed loop of the parameters of the engine is realized, the dependence on the parameters of the airplane is eliminated, the reconstruction reliability of the parameters of the engine is improved, and the method has great significance for the fault diagnosis and treatment countermeasure formulation of the fault control system of the engine.
The second aspect of the present application provides a reconstruction device corresponding to the above method when the total air intake temperature of the aero-engine fails, mainly including:
the total pressure acquisition module is used for acquiring the total inlet pressure of the fan of the turbofan engine, and the total outlet temperature and the total outlet pressure of the air compressor;
the fitting module is used for fitting the variable compression efficiency based on the total inlet pressure of the turbofan engine fan and the total outlet pressure of the compressor;
and the reconstruction module is used for establishing an air inlet total temperature reconstruction model of the turbofan engine fan based on the variable compression efficiency, the inlet total pressure of the turbofan engine fan, the outlet total temperature of the air compressor and the outlet total pressure.
Preferably, the reconstruction module relates to a reconstruction model as follows:
wherein:T t2 the total temperature of the air inlet of the fan is used,T t3 is the total temperature of the outlet of the air compressor,P t2 is the total pressure of the inlet of the fan,P t3 Is the total pressure of the outlet of the air compressor, k is the specific heat ratio, E c Is a variable compression efficiency.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in 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 (8)
1. The reconstruction method for the total air inlet temperature fault of the aero-engine is characterized by comprising the following steps of:
step S1: acquiring the total inlet pressure of a fan of a turbofan engine, and the total outlet temperature and the total outlet pressure of a compressor;
step S2: fitting a variable compression efficiency based on an inlet total pressure of the turbofan engine fan and an outlet total pressure of the compressor;
step S3: and establishing an air inlet total temperature reconstruction model of the turbofan engine fan based on the variable compression efficiency, the inlet total pressure of the turbofan engine fan, the outlet total temperature of the compressor and the outlet total pressure.
2. The method for reconstructing an aircraft engine intake total temperature event as set forth in claim 1, wherein said variable compression efficiency is obtained by a function of a high altitude bench test data fit.
3. The method of reconstructing an aircraft engine intake total temperature event as set forth in claim 2, wherein said function comprises a 2-degree function.
4. The method according to claim 1, wherein in the step S3, an intake total temperature reconstruction model of the turbofan engine fan is established based on the variable compression efficiency, the total inlet pressure of the turbofan engine fan, the total outlet temperature of the compressor and the total outlet pressure, and the specific model is as follows:
wherein: t (T) t2 For the total temperature of the air inlet of the fan, T t3 Is the total temperature of the outlet of the air compressor, P t2 For the total pressure, P, of the inlet of the fan t3 Is the total pressure of the outlet of the air compressor, k is the specific heat ratio, E c Is a variable compression efficiency.
5. The method for reconstructing an aircraft engine intake total temperature event as recited in claim 4, wherein k has a value of 1.4.
6. The method for reconstructing an aircraft engine intake total temperature event as recited in claim 2 wherein said altitude bench test data is stripped of outliers.
7. The method of reconstructing an aircraft engine intake total temperature event as set forth in claim 2, wherein said function comprises an equality relationship function of said polytropic compression efficiency, an inlet total pressure of said turbofan engine fan, and an outlet total pressure of said compressor.
8. The method for reconstructing an aircraft engine intake total temperature event as set forth in claim 7, wherein said turbofan engine fan intake total pressure and said compressor outlet total pressure are in a proportional relationship in said equality relationship function.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111394455.2A CN113899559B (en) | 2021-11-23 | 2021-11-23 | Reconstruction method and device for air inlet total temperature fault of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111394455.2A CN113899559B (en) | 2021-11-23 | 2021-11-23 | Reconstruction method and device for air inlet total temperature fault of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113899559A CN113899559A (en) | 2022-01-07 |
| CN113899559B true CN113899559B (en) | 2023-06-20 |
Family
ID=79195032
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111394455.2A Active CN113899559B (en) | 2021-11-23 | 2021-11-23 | Reconstruction method and device for air inlet total temperature fault of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113899559B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114893300B (en) * | 2022-04-14 | 2023-10-13 | 北京动力机械研究所 | Parameter control pressure parameter judging method and redundancy control method for small turbofan engine |
| CN114893301B (en) * | 2022-04-14 | 2023-09-08 | 北京动力机械研究所 | Parameter control temperature parameter judging method and redundancy control method for small turbofan engine |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110080884B (en) * | 2018-10-31 | 2020-07-07 | 南京航空航天大学 | Turbofan engine hot end virtual sensor signal generation and gas circuit fault diagnosis method |
| CN110320799B (en) * | 2019-06-13 | 2021-05-07 | 大连理工大学 | Undisturbed cut-in fault-tolerant control method for faults of aircraft engine actuator |
| CN112069602B (en) * | 2020-09-14 | 2022-08-26 | 中国人民解放军国防科技大学 | Reverse reconstruction method, device, medium and equipment for total temperature of spray pipe inlet |
| CN113515900A (en) * | 2021-04-07 | 2021-10-19 | 南京航空航天大学 | Numerical simulation method for simulating wake flow of continuous rotation detonation engine |
| CN113361040B (en) * | 2021-06-18 | 2024-01-02 | 中国航发沈阳发动机研究所 | Combustion chamber outlet temperature evaluation method under complete engine condition |
| CN113419575B (en) * | 2021-06-29 | 2022-11-22 | 中国航发沈阳发动机研究所 | Control method for improving aerodynamic stability of shipboard aircraft engine during takeoff |
-
2021
- 2021-11-23 CN CN202111394455.2A patent/CN113899559B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN113899559A (en) | 2022-01-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113899559B (en) | Reconstruction method and device for air inlet total temperature fault of aero-engine | |
| CN110717219B (en) | Method and device for acquiring inlet flow of air compressor in complete machine state of aero-engine | |
| US8014929B2 (en) | Method of monitoring a gas turbine engine | |
| EP2388672B1 (en) | Identifying of turbomachine faults | |
| US20100024536A1 (en) | Methods and systems for estimating operating parameters of an engine | |
| CA2956999C (en) | Automated system and method for generating engine test cell analytics and diagnostics | |
| US11293353B2 (en) | Transient control to extend part life in gas turbine engine | |
| US9896961B2 (en) | Use of ss data trends in fault resolution process | |
| Andoga et al. | A digital diagnostic system for a small turbojet engine | |
| CN114459762B (en) | Rocket engine health state diagnosis system and method | |
| CN106525442B (en) | A kind of method and device monitoring gas turbine gas circuit performance | |
| CN110080884B (en) | Turbofan engine hot end virtual sensor signal generation and gas circuit fault diagnosis method | |
| CN102944789B (en) | A kind of fanjet complete machine electrical system Gernral Check-up device and method | |
| Agrawal et al. | An analysis procedure for the validation of on-site performance measurements of gas turbines | |
| CN110609479B (en) | Gas turbine sensor fault-tolerant control method based on linear variable parameter model | |
| Zhao et al. | Hardware-in-the-loop simulation platform for fault diagnosis of rocket engines | |
| Frith | The effect of compressor rotor tip crops on turboshaft engine performance | |
| Frith | The effect of compressor rotor tip crops on turboshaft engine performance | |
| US20240094067A1 (en) | Systems and methods for determining gas turbine engine temperatures | |
| Danielsson | Gas Path Analysis Applied to Pre and Post Overhaul Testing of JT9D Turbofan Engine | |
| CN114756003A (en) | Variable cycle engine resolution redundancy design method | |
| US20230184176A1 (en) | System and method for synthesizing engine thrust | |
| CN114266116A (en) | Matching method and system of turbocharger and engine and electronic equipment | |
| Koessler | Experimental investigation of high-pressure steam induced stall of a transonic rotor | |
| CN114048633A (en) | Airplane high and cold test matrix design method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |