CN113899559A - Reconstruction method and device for failure of total air inlet temperature of aero-engine - Google Patents
Reconstruction method and device for failure of total air inlet temperature of aero-engine Download PDFInfo
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Abstract
The application belongs to the field of engine fault detection and processing, and particularly relates to a reconstruction method and a reconstruction device for an aero-engine air inlet total temperature fault, wherein the method comprises the following steps: step S1: acquiring inlet total pressure of a fan of a turbofan engine, outlet total temperature of a compressor and outlet total pressure; step S2: fitting a polytropic compression efficiency based on the inlet total pressure of the turbofan engine fan and the 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, wherein parameters such as the height H, Ma input by an airplane are not needed during parameter reconstruction, so that the self parameter reconstruction closed loop of the engine is realized, the dependence on airplane parameters is eliminated, the reliability of the self parameter reconstruction of the engine is improved, and the method has great significance for fault diagnosis and treatment strategy formulation of an engine fault control system.
Description
Technical Field
The application belongs to the field of engine fault detection and processing, and particularly relates to a reconstruction method and device for air inlet total temperature fault under the complex working condition of full envelope of an aircraft engine.
Background
A new generation of advanced small bypass ratio turbofan engine control system adopts a dual-redundancy full-authority digital electronic control form, and has no mechanical hydraulic backup, so higher requirements are put forward for fault diagnosis and treatment countermeasures, wherein the total air inlet temperature of a fan is used as the most main control parameter of the engine, if a fan total air inlet temperature sensor fails, a model needs to be established to calculate and reconstruct the total air inlet temperature of the fan, and the calculated total air inlet temperature ensures that the engine can work safely within a certain range.
The existing total inlet temperature reconstruction method adopts parameters such as 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 problem, a first aspect of the present application provides a reconstruction method for an aircraft engine air intake total temperature fault, including the following steps:
step S1: acquiring inlet total pressure of a fan of a turbofan engine, outlet total temperature of a compressor and outlet total pressure;
step S2: fitting a polytropic compression efficiency based on the inlet total pressure of the turbofan engine fan and the 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 fitted by high-altitude bench test data.
Preferably, the function comprises a 2-degree function.
Preferably, in step S3, a total intake temperature reconstruction model of the turbofan engine fan is established based on the polytropic 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 t2is the total temperature of the air intake of the fan,T t3is the total temperature of the outlet of the gas compressor,P t2is the total pressure of the inlet of the fan,P t3Total pressure at the outlet of the compressor, k is specific heat ratio, EcIs the polytropic compression efficiency.
Preferably, k has a value of 1.4.
Preferably, the high-altitude platform test data is free of outlier points.
Preferably, the function comprises an equality function of the polytropic compression efficiency, the total inlet pressure of the turbofan engine fan and the total outlet pressure of the compressor.
Preferably, the inlet total pressure of the turbofan engine fan is in a proportional relationship with the outlet total pressure of the compressor in the equality function.
The application provides a reconstruction device corresponding to the method for total temperature fault of air inlet of an aircraft engine in a second aspect, and the reconstruction device mainly comprises:
the total pressure acquisition module is used for acquiring the total inlet pressure of a fan of the turbofan engine, the total outlet temperature of the compressor and the total outlet pressure;
the fitting module is used for fitting the polytropic compression efficiency based on the total inlet pressure of the turbofan engine fan and the total outlet pressure of the compressor;
the reconstruction module is used for establishing an air inlet total temperature reconstruction model of the turbofan engine fan based on the changeable 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 that is:
wherein:T t2is the total temperature of the air intake of the fan,T t3is the total temperature of the outlet of the gas compressor,P t2is the total pressure of the inlet of the fan,P t3Total pressure at the outlet of the compressor, k is specific heat ratio, EcIs the polytropic compression efficiency.
The advantages of the present application include: the method calculates and reconstructs the total inlet air temperature parameter through the engine measurement parameter, realizes the accurate reconstruction of the total inlet air temperature of the aircraft engine under the complex working condition of full envelope, solves the problem that the control of the aircraft engine under the full-authority digital electronic control is not accurate when the total inlet air temperature is in fault, does not need parameters such as height H, Ma input by an airplane during the parameter reconstruction, realizes the self parameter reconstruction closed loop of the engine, eliminates the dependence on the airplane parameters, improves the reliability of the self parameter reconstruction of the engine, and has great significance for the fault diagnosis and treatment strategy 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
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 application provides a reconstruction method for failure of total temperature of air inlet of an aircraft engine in a first aspect, which comprises the following steps:
step S1: acquiring inlet total pressure of a fan of a turbofan engine, outlet total temperature of a compressor and outlet total pressure, and regarding the turbofan engine as a compression part when engine characteristics are approximately calculated, wherein the fan is connected with the compressor, as shown in figure 1;
step S2: fitting a polytropic compression efficiency based on the inlet total pressure of the turbofan engine fan and the outlet total pressure of the compressor; wherein the polytropic compression efficiency is EcCan be obtained by fitting test data of the high-altitude station and by analysis, EcMainly, the functional relation related to Pt 3/Pt 2 is generally fit to a function of degree 2, and taking a certain type of engine as an example, the fit function is obtained as follows:
the curve is shown in figure 2.
Step S3: establishing a total inlet temperature reconstruction model of the turbofan engine fan 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, wherein the total inlet temperature reconstruction 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 total pressure of the inlet and the outlet can be obtained by measurement, whenT t2When measuring faults, canT t3 、P t2、P t3And calculating reconstruction by the following method:
substituting the fitted polytropic compression efficiency into the model to obtain a final reconstruction model:
wherein,T t2is the total temperature of the air intake of the fan,T t3is the total temperature of the outlet of the gas compressor,P t2is the total pressure of the inlet of the fan,P t3Total pressure at the outlet of the compressor, k is specific heat ratio, EcIs the polytropic compression efficiency.
When k takes 1.4, we get:
when the parameters of the invention are reconstructed, parameters such as the height H, Ma input by an airplane are not needed, the self-parameter reconstruction closed loop of the engine is realized, the dependence on the airplane parameters is eliminated, the reliability of the self-parameter reconstruction of the engine is improved, and the invention has great significance for fault diagnosis and disposal strategy formulation of an engine fault control system.
The application provides a reconstruction device corresponding to the method for total temperature fault of air inlet of an aircraft engine in a second aspect, and the reconstruction device mainly comprises:
the total pressure acquisition module is used for acquiring the total inlet pressure of a fan of the turbofan engine, the total outlet temperature of the compressor and the total outlet pressure;
the fitting module is used for fitting the polytropic compression efficiency based on the total inlet pressure of the turbofan engine fan and the total outlet pressure of the compressor;
the reconstruction module is used for establishing an air inlet total temperature reconstruction model of the turbofan engine fan based on the changeable 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 that is:
wherein:T t2is the total temperature of the air intake of the fan,T t3is the total temperature of the outlet of the gas compressor,P t2is the total pressure of the inlet of the fan,P t3Total pressure at the outlet of the compressor, k is specific heat ratio, EcIs the polytropic compression efficiency.
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 (10)
1. A reconstruction method for total temperature fault of air inlet of an aircraft engine is characterized by comprising the following steps:
step S1: acquiring inlet total pressure of a fan of a turbofan engine, outlet total temperature of a compressor and outlet total pressure;
step S2: fitting a polytropic compression efficiency based on the inlet total pressure of the turbofan engine fan and the 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 reconstruction method for the total temperature of air intake of the aircraft engine according to claim 1, wherein the polytropic compression efficiency is obtained by a function of high altitude platform test data fitting.
3. The method of reconstructing at time of total air intake temperature fault of an aircraft engine as claimed in claim 2, wherein said function comprises a 2-degree function.
4. The reconstruction method for the total inlet temperature of the aircraft engine according to claim 1, wherein in the step S3, a total inlet temperature reconstruction model of the turbofan engine fan is established based on the polytropic 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 reconstruction model specifically comprises:
wherein:T t2is the total temperature of the air intake of the fan,T t3is the total temperature of the outlet of the gas compressor,P t2is the total pressure of the inlet of the fan,P t3Total pressure at the outlet of the compressor, k is specific heat ratio, EcIs the polytropic compression efficiency.
5. The reconstruction method of the total temperature of air inlet of the aircraft engine in the fault condition as claimed in claim 4, wherein k takes a value of 1.4.
6. The reconstruction method in the event of an aircraft engine intake total temperature fault according to claim 2, characterized in that the high altitude platform test data is deprived of outlier points.
7. The method of reconstructing an aircraft engine inlet total temperature fault condition as claimed in claim 2, wherein said function comprises an equality function of said polytropic compression efficiency, said inlet total pressure of said turbofan engine fan and said outlet total pressure of said compressor.
8. The method of reconstructing an aircraft engine inlet total temperature fault as claimed in claim 7, wherein an inlet total pressure of the turbofan engine fan and an outlet total pressure of the compressor are in a proportional relationship in the equality function.
9. A reconsitution device during aeroengine total temperature of admitting air trouble, its characterized in that includes:
the total pressure acquisition module is used for acquiring the total inlet pressure of a fan of the turbofan engine, the total outlet temperature of the compressor and the total outlet pressure;
the fitting module is used for fitting the polytropic compression efficiency based on the total inlet pressure of the turbofan engine fan and the total outlet pressure of the compressor;
the reconstruction module is used for establishing an air inlet total temperature reconstruction model of the turbofan engine fan based on the changeable compression efficiency, the inlet total pressure of the turbofan engine fan, the outlet total temperature of the air compressor and the outlet total pressure.
10. The device for reconstructing the total temperature of air inlet of the aircraft engine during the fault according to claim 9, wherein the reconstruction module relates to a reconstruction model which is as follows:
wherein:T t2is the total temperature of the air intake of the fan,T t3is the total temperature of the outlet of the gas compressor,P t2is the total pressure of the inlet of the fan,P t3Total pressure at the outlet of the compressor, k is specific heat ratio, EcIs the polytropic compression efficiency.
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