CN114861405A - Airworthiness conformance verification method for power transient of aircraft engine - Google Patents
Airworthiness conformance verification method for power transient of aircraft engine Download PDFInfo
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Abstract
The invention discloses a airworthiness conformance verification method for power transient of an aircraft engine, which comprises the following steps of: determining a limit condition of the influence of power transient on the stability margin in the working process of the aeroengine; obtaining an analysis program capable of simulating a stability margin change rule under power transient of the aero-engine; performing transient simulation on the aircraft engine in the power transient process; analyzing the change rule of the stability margin of the aero-engine along with time in the power transient simulation process, and determining the working moment of the limit value of the stability margin and the flow of the aero-engine at the moment; according to the method for verifying the conformity of the aviation engine power transient, provided by the invention, the operability is strong, the seaworthiness conformity analysis can be quickly and economically carried out on the power transient process of the aviation engine with different configurations, and thus the conformity verification process of the stability of the military and civil aviation engine is supported.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a airworthiness conformity verification method for aero-engine power transient.
Background
When a modern aviation aircraft executes flying tasks such as take-off, climbing and landing, the angle of the throttle lever needs to be adjusted, so that the aviation engine provides variable power to meet the requirements of the tasks. At the moment, the rotating speed of a rotating shaft of the aircraft engine changes due to the change of the combustion state in the combustion chamber, the power provided by the turbine and the power demand of the compressor are instantaneously unbalanced, so that the working state point of the compressor is dynamically changed, the instantaneous stability margin of a compression system is influenced, the problems of stall, surge and the like are caused in serious conditions, and the flight safety is damaged. The aviation management organizations at home and abroad take the power transient as one of stability reduction factors, and are listed in the stability evaluation category, and make corresponding regulations on the requirements of stability in airworthiness terms.
The relevant airworthiness requirements for surge and stall are indicated in article CCAR33.65, civil aviation regulations in china, where determining the effect of a destabilising factor on stability is one of the key activities for airworthiness compliance verification. The GJB/Z224-. At present, the stability reduction factor of the power transient has higher attention degree in the airworthiness field, but no clear regulation is made on a conformity analysis method and a verification process of the power transient. In the process of airworthiness evidence obtaining, how to adopt a reasonable and efficient conformity analysis method to determine a conformity verification process of power transient is a key for showing the conformity of the aero-engine.
In the prior art, stability evaluation under the influence of power transient is carried out on a civil turbofan engine with a large bypass ratio, and airworthiness conformance is verified to be the closest evaluation method to the technical scheme described in the invention, but the scheme in the prior art lacks a general program for evaluating aeroengines with different configurations and combining airworthiness approval.
Disclosure of Invention
The present invention is directed to solving, to some extent, one of the technical problems in the related art. Therefore, the airworthiness conformance verification method for the power transient of the aero-engine is provided, has strong operability, and can quickly and economically analyze the airworthiness conformance of the power transient process of the aero-engine with different configurations so as to support the conformance verification process of the stability of the military and civil aero-engines.
In order to achieve the above object, the present invention provides a airworthiness compliance verification method for an aircraft engine power transient, comprising the following operation steps:
s1: determining a limit condition of the influence of power transient on the stability margin in the working process of the aeroengine;
s2: obtaining an analysis program capable of simulating a stability margin change rule under the power transient of the aircraft engine;
s3: performing transient simulation on the aircraft engine in the power transient process;
s4: analyzing the change rule of the stability margin of the aero-engine along with time in the power transient simulation process in the step S3, and determining the working moment of the limit value of the stability margin and the flow of the aero-engine at the moment; and (5) according to the limit condition of the influence of the power transient on the stability margin in the step S1, simultaneously analyzing the change rule of the stability margin calculated in the step S2, and determining the airworthiness conformity of the aero-engine under the power transient.
In a preferred embodiment, the determination of the limit conditions in step S1 includes the determination and comparison of surge and stall.
In a preferred embodiment, the determining the basis for the limiting condition in step S1 includes: the operating environment of the aircraft, the flight mission and the type of aircraft engine fitted, wherein,
the working environment of the aircraft comprises: altitude and mach number;
the flight mission comprises the following steps: rapid acceleration and rapid deceleration;
the aircraft engine types include: split turbofan engines, mixed-row turbofan engines, turbojet engines, turboshaft engines, and turboprop engines.
In a preferred embodiment, in step S2, the component modules required by the aircraft engine are recalled from the library according to the aircraft-assembled aircraft engine type in step S1; and simultaneously inputting parameters of all parts of the aero-engine into the corresponding modules, wherein the parameters of all parts of the aero-engine comprise a performance map, pneumatic parameters and geometric parameters.
In a preferred embodiment, in step S3, an aircraft engine power transient is determined according to the flight mission and the aircraft engine type of the aircraft determined in step S1, the process is modeled, and specific parameters of the power transient are input into a dynamic module of an analysis program, so as to realize transient simulation of the aircraft engine in the power transient.
In a preferred embodiment, in step S2, the method includes selecting a component module of the aircraft engine to establish a stability analysis program, and obtaining an analysis program for simulating a variation law of the stability margin under the power transient of the aircraft engine, and specifically includes the following steps:
SS1, entering an MATLAB SIMULINK module layer, and building a calculation module of the core component of the aero-engine to form a User module library;
selecting a built and packaged component module for lapping according to the type of the aero-engine subjected to airworthiness conformance verification;
SS2, inputting the performance map of the component at the bottom layer of each component module, and inputting boundary condition constraint parameters at the inlet and outlet of the component module;
and SS3, establishing a component matching relation based on the type of the aero-engine, determining a common working equation of the aero-engine, inputting parameters such as mechanical shaft transmission efficiency and the like in a program solving layer, and improving program fidelity.
In a preferred embodiment, in the step of SS1, the component modules comprise an air inlet, a compressor, a combustion chamber, a turbine and a tail nozzle, and a multi-stage compressor and turbine module connection is required for a double-shaft or three-shaft aircraft engine;
in the SS2 step, the constraint parameters of the boundary conditions comprise the temperature, the pressure and the flow at the part inlet and the sectional area of the interface between the parts, and after the boundary conditions of the module are completely defined, the calling of the single part can be completed to simulate the part performance of the aero-engine;
in the step of SS3, the common working equations include flow balance, pressure balance, physical speed identity and power balance.
In a preferred embodiment, in step S3, the simulation of the transient state of the aircraft engine during the power transient using the stability analysis program includes the following steps:
a: calling a dynamic module in an aircraft engine stability analysis program, adding a rotor dynamics equation to determine the real-time matching relationship of parts, wherein the common working equation of the aircraft engine changes at the moment, the residual power caused by the change of oil supply along with time in the dynamic effect is considered, the power balance condition is not applicable any more, and the power transient process at the moment can be described as shown in the following formula:
wherein, in the formula: n is the physical rotation speed of the engine shaft, J is the moment of inertia of the rotating part, t is time, eta is the mechanical efficiency of the rotating shaft, Pow T Power supplied to the turbine, Pow acc Load, the amount of power draw required for engine accessory operation C Rotating a load for an engine compressor;
b: modeling specific parameters of a power transient according to specific operating conditions of the aircraft engine.
In a preferred embodiment, the specific parameters of the modeled power transient include: a power transient type, a total duration of the power transient, a power rate of change of the power transient, and an initial speed of the power transient, the power transient type including a rapid acceleration and/or a rapid deceleration.
In a preferred embodiment, in step S4, determining the airworthiness of the aircraft engine under the power transient specifically includes the following process:
a: analyzing a change rule of the stability margin in the power transient process, and determining a limit value and a corresponding position of the stability margin in the power transient process;
b: in comparison with the limit condition of the impact of the power transient on the stability margin in step S1, the compliance under the aircraft engine power transient is determined as follows:
ΔSM PLA，req ≤ΔSM PLA，avai ；
wherein, in the formula: delta SM PLA，req For variation of stability margin under power transient in actual conditions, Δ SM PLA，avai The allowable value of stability margin under power transients specified in airworthiness terms.
The invention has the beneficial effects that: compared with the traditional method, the method can judge the influence of power transient on the stability of the aeroengine with various configurations in different flight tasks, and combines the stability analysis program of the aeroengine with the stability margin requirement of the airworthiness term, so as to establish the airworthiness conformity verification process and provide reference for the conformity verification process of the aeroengine power transient.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is an overall flow chart of a method for verifying airworthiness of an aircraft engine power transient according to an embodiment of the invention;
FIG. 2 is a schematic view of a typical small and medium aircraft engine flight envelope for aircraft engine power transients in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram of an air inlet channel in a part module of a stability analysis program of a small and medium-sized aircraft engine according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a combustion chamber in a part module of a stability analysis program of a small and medium-sized aero-engine according to the airworthiness conformance verification method for power transient of an aero-engine in an embodiment of the present invention;
FIG. 5 is a schematic diagram of a compressor in a small and medium-sized aircraft engine stability analysis program component module according to the airworthiness conformance verification method for aircraft engine power transients in an embodiment of the present invention;
FIG. 6 is a schematic diagram of a turbine in a part module of a stability analysis program of a small and medium-sized aircraft engine according to an embodiment of the invention;
FIG. 7 is a diagram of the fueling laws specified in the airworthiness review of a small and medium-sized aero-engine of the method for verifying the airworthiness of the power transient of an aero-engine according to the embodiment of the present invention;
FIG. 8 is a graph of the change law of the transient working line in the power transient process of the aircraft engine according to the airworthiness conformance verification method for the power transient of the aircraft engine of the embodiment of the present invention;
FIG. 9 is a graph of variation law of stability margin in the process of transient power variation of an aircraft engine according to the airworthiness conformance verification method for transient power of the aircraft engine.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary and intended to be illustrative of the present invention and should not be construed as limiting the present invention, and all other embodiments that can be obtained by one skilled in the art based on the embodiments of the present invention without inventive efforts shall fall within the scope of protection of the present invention.
Example 1
Referring to fig. 1-9, a method for verifying airworthiness of an aircraft engine power transient according to an embodiment of the present invention includes the following steps:
s1: determining a limit condition of the influence of power transient on the stability margin in the working process of the aeroengine;
s2: obtaining an analysis program capable of simulating a stability margin change rule under the power transient of the aircraft engine;
s3: performing transient simulation on the aircraft engine in the power transient process;
s4: analyzing the change rule of the stability margin of the aero-engine along with time in the power transient simulation process in the step S3, and determining the working moment of the limit value of the stability margin and the flow of the aero-engine at the moment; and (5) according to the limit condition of the influence of the power transient on the stability margin in the step S1, simultaneously analyzing the change rule of the stability margin calculated in the step S2, and determining the airworthiness conformity of the aero-engine under the power transient.
The determination of the limit conditions in step S1 includes the determination and comparison of surge and stall.
The determination of the basis in the limit condition in the step S1 includes: the operating environment of the aircraft, the flight mission and the type of aircraft engine fitted, wherein,
the working environment of the aircraft comprises: altitude and mach number;
the flight mission comprises the following steps: rapid acceleration and rapid deceleration;
the aircraft engine types include: a split-row turbofan engine, a mixed-row turbofan engine, a turbojet engine, a turboshaft engine, and/or a turboprop engine.
In step S2, component modules required for the aircraft engine are retrieved from the library according to the aircraft-equipped aircraft engine type in step S1; and simultaneously inputting parameters of all parts of the aero-engine into the corresponding modules, wherein the parameters of all parts of the aero-engine comprise a performance map, pneumatic parameters and geometric parameters.
In step S3, according to the flight mission and/or the type of the aircraft engine determined in step S1, an aircraft engine power transient is determined and modeled, and specific parameters of the power transient are input into a dynamic module of an analysis program, so as to realize transient simulation of the aircraft engine in the power transient.
In step S2, a stability analysis program is established by selecting a component module of the aircraft engine to obtain an analysis program that can simulate a change law of the stability margin under the power transient of the aircraft engine, and the method specifically includes the following steps:
SS1, entering an MATLAB SIMULINK module layer, and building a calculation module of the core component of the aero-engine to form a User module library;
selecting a built and packaged component module for lapping according to the type of the aero-engine subjected to airworthiness conformance verification;
SS2, inputting the performance map of the component at the bottom layer of each component module, and inputting boundary condition constraint parameters at the inlet and outlet of the component module;
and SS3, establishing a component matching relation based on the type of the aero-engine, determining a common working equation of the aero-engine, inputting parameters such as mechanical shaft transmission efficiency and the like in a program solving layer, and improving program fidelity.
In the SS1 step, the component modules comprise an air inlet channel, a gas compressor, a combustion chamber, a turbine and a tail nozzle, and the multistage gas compressor and the turbine module are required to be connected aiming at a double-shaft or three-shaft aero-engine;
in the SS2 step, the boundary condition constraint parameters comprise the temperature, the pressure and the flow at the part inlet and the sectional area of the interface between the parts, and after the boundary conditions of the module are completely defined, the calling of the single part can be completed, and the part performance of the aero-engine can be simulated;
in the step of SS3, the common working equations include flow balance, pressure balance, physical speed identity and power balance.
In step S3, the simulation of the transient state of the aircraft engine during the power transient using the stability analysis program includes the following processes:
a: calling a dynamic module in an aircraft engine stability analysis program, adding a rotor dynamics equation to determine the real-time matching relationship of parts, wherein the common working equation of the aircraft engine changes at the moment, the residual power caused by the change of oil supply along with time in the dynamic effect is considered, the power balance condition is not applicable any more, and the power transient process at the moment can be described as shown in the following formula:
wherein, in the formula: n is the physical rotation speed of the engine shaft, J is the moment of inertia of the rotating part, t is time, eta is the mechanical efficiency of the rotating shaft, Pow T Power supplied to the turbine, Pow acc Load, the amount of power draw required for engine accessory operation C Rotating a load for an engine compressor;
b: modeling specific parameters of a power transient according to specific operating conditions of the aircraft engine.
Specific parameters of the modeled power transient include: a power transient type, a total duration of the power transient, a power change rate of the power transient, and an initial speed of the power transient, the power transient type including rapid acceleration and rapid deceleration.
In step S4, determining the airworthiness compliance of the aircraft engine under the power transient specifically includes the following process:
a: analyzing a change rule of the stability margin in the power transient process, and determining a limit value and a corresponding position of the stability margin in the power transient process;
b: in comparison with the limit condition of the impact of the power transient on the stability margin in step S1, the compliance under the aircraft engine power transient is determined as follows:
ΔSM PLA，req ≤ΔSM PLA，avai ；
wherein, in the formula: Δ SM PLA，req Is the work in the actual working conditionVariation of stability margin under rate transient, Δ SM PLA，avai The allowable value of stability margin under power transients specified in airworthiness terms.
Example 2
Referring to fig. 1-9, a method for verifying airworthiness of an aircraft engine power transient according to an embodiment of the present invention includes the following steps:
step (1): according to the working environment, flight mission and the type of an assembled aero-engine of an aircraft, wherein the working environment is flight altitude and Mach number, the flight mission is rapid acceleration and rapid deceleration, and the type of the aero-engine comprises a split turbofan engine, a mixed turbofan engine, a turbojet engine and a turboshaft/turboprop engine; determining the limit condition of the influence of power transient on stability margin in the working process of an aeroengine according to relevant requirements of CCAR33-R2 item 65 on surge and stall;
step (2): calling component modules required by the aircraft engine from a library according to the type of the aircraft engine assembled in the step (1); inputting parameters of all parts of the aircraft engine into corresponding modules, wherein the parameters comprise a performance map, pneumatic parameters and geometric parameters; obtaining an analysis program capable of simulating a stability margin change rule under the power transient of the aircraft engine;
and (3): determining the power transient process of the aircraft engine according to the flight mission of the aircraft and the type of the aircraft engine determined in the step (1), modeling the process, inputting specific parameters of the power transient process into a dynamic module of an analysis program, and performing transient simulation on the aircraft engine in the power transient process;
and (4):
analyzing the change rule of the stability margin of the aero-engine along with time in the power transient process in the step (3), and determining the working moment of the limit value of the stability margin and the flow of the aero-engine at the moment;
and (3) finally determining the airworthiness conformity of the aircraft engine to the airworthiness clause CCAR33.65 under the power transient according to the requirements of the airworthiness clause on the stability margin in the step (1) and the stability margin change rule calculated in the analysis program.
In the step (2), a component module of the aircraft engine is selected to establish a stability analysis program, and an analysis program capable of simulating a stability margin change rule under the power transient of the aircraft engine is obtained, wherein the specific process is as follows:
(1) entering an MATLAB SIMULINK module layer, and building a calculation module of the core component of the aero-engine to form a User module library; according to the type of the aero-engine for verifying the airworthiness conformance, a built and packaged component module is selected for lapping, the component module comprises an air inlet channel, a gas compressor, a combustion chamber, a turbine, a tail nozzle and the like, and the double-shaft or three-shaft aero-engine needs to be connected with a multi-stage gas compressor and a turbine module;
(2) inputting a performance map of the component at the bottom layer of each component module, inputting boundary condition constraint parameters at an inlet and an outlet of the component module, wherein the parameters comprise temperature, pressure, flow, sectional area of an interface between the components and the like at the inlet of the component, and after completely defining the boundary conditions of the module, calling of the individual component can be completed, and the component performance of the aircraft engine can be simulated;
(3) establishing a component matching relation based on the type of the aero-engine, and determining a common working equation of the aero-engine, wherein the equation comprises flow balance, pressure balance, same physical rotating speed and power balance. And parameters such as transmission efficiency of the mechanical shaft and the like are input into a program solving layer, so that the program fidelity is improved.
In the step (3), a specific process of simulating the instantaneous state of the aircraft engine in the power transient process by applying a stability analysis program is as follows:
(1) calling a dynamic module in an aircraft engine stability analysis program, adding a rotor dynamics equation to determine the real-time matching relationship of parts, wherein the common working equation of the aircraft engine changes at the moment, the residual power caused by the change of oil supply along with time in the dynamic effect is considered, the power balance condition is not applicable any more, and the transient process of the power at the moment can be described as shown in the following formula:
wherein, in the formula: n is the physical rotation speed of the engine shaft, J is the moment of inertia of the rotating part, t is time, eta is the mechanical efficiency of the rotating shaft, Pow T Power supplied to the turbine, Pow acc Load, the amount of power draw required for engine accessory operation C And rotating load of the compressor of the engine.
(2) Modeling specific parameters of a power transient in accordance with specific operating conditions of an aircraft engine, said parameters comprising: power transient type (jerk/decelerate), total duration of power transient, rate of change of power for power transient, initial speed of power transient.
In the step (4), the specific process for determining the airworthiness compliance under the power transient of the aircraft engine is as follows:
(1) analyzing a change rule of the stability margin in the power transient process, and determining a limit value and a corresponding position of the stability margin in the power transient process;
(2) and (3) comparing the stability margin limit condition determined by the airworthiness clause in the step (1), namely the allowable value, and determining the conformity of the aircraft engine under the power transient condition, wherein the conformity is shown as the following formula:
ΔSM PLA，req ≤ΔSM PLA，avai ；
wherein, in the formula: delta SM PLA，req For variation of stability margin under power transient in actual conditions, Δ SM PLA，avai The allowable value of stability margin under power transients as specified in airworthiness clauses.
Example 3
The present invention will be described in further detail below with reference to the accompanying fig. 1-9. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Referring to a typical flight envelope diagram of a small and medium-sized aircraft engine shown in fig. 2, in the stages of take-off, climbing, sliding, landing and the like in the flight envelope, the power level of the engine is adjusted by increasing or decreasing the angle of the throttle lever along with the instantaneous change of the power of the aircraft engine, and in the stage, the instantaneous change of the throttle lever cannot be matched in real time due to the inertia of a rotor, so that the supply and demand relationship of the internal power of the engine is influenced, and the airworthiness of the engine is required to be verified; according to the requirements for stability margins in the CCAR33.65 regulations for civil aviation in china, at any point within the engine operating envelope, start-up, change in power or thrust, increase in power or thrust, extreme intake distortion or intake temperature must not cause surge or stall to the point where flameout, structural failure, over-temperature or unrecoverable engine power or thrust occurs.
In the implementation case, a turboshaft engine of a certain model is selected for research, and the design point parameters of the engine are shown in the table below.
The table is a design point parameter of a certain type of aeroengine.
| Parameter name | Parameter value |
| Inlet flow rate | 2.475kg/s |
| Pressure ratio of compressor | 7.88 |
| Power of | 573kW |
| Gas turbine rotational speed | 51800rpm |
| Free turbine speed | 41586rpm |
| Mechanical efficiency | 0.99 |
| Oil consumption | 0.385kg/h |
Referring to the relevant schematic diagrams of the stability analysis program component modules shown in fig. 3-6, which show the SIMULINK schematic diagrams of some modules, the present embodiment provides a stability analysis program satisfying the requirements of medium and small-sized aeroengine configurations, and the program comprises component modules such as an air inlet, an air compressor, a combustion chamber, a power turbine, a free turbine, a tail nozzle and the like; through testing, the analysis program can complete the calculation simulation of the whole machine, and the integral error between the analysis result and the test data is not more than 5%.
Referring to an oil supply rule diagram specified in airworthiness examination of a small and medium-sized aero-engine shown in FIG. 7, the oil supply rule is selected from the regulations of an airworthiness examination subject on power transient, the initial rotating speed, the duration of an acceleration/deceleration process and the duration of a middle stabilization process in the power transient process are constrained, and rotor dynamics constraint in a dynamic module is completed according to parameters such as the rotor moment of inertia, the compressor load and the accessory extraction power of a certain aero-engine adopted in a case.
According to the dynamic module simulation result of the stability analysis program in the disclosure, the change rule diagram of the transient working line under the power transient of the aero-engine shown in fig. 8 can be obtained, the stability is analyzed, and the change rule of the stability margin along with the flow of the working point under the power transient of the aero-engine is obtained.
Finally, according toThe fuel supply rule graph can obtain a stability margin change rule graph in the power transient process of the aero-engine, can determine the attenuation values of the stability margin under different rotating speeds in the transient process, and combines the actual application of the aero-engine and the provision of airworthiness terms, wherein the stability margin delta SM required by the power transient of the engine of the type in the rapid acceleration process PLA，avai 2%, the actual margin of stability variation Δ SM calculated PLA，req At 1.8%, the airworthiness compliance of this model engine to the terms of CCAR33.65 under power transient conditions was determined from the above results.
Wherein, Δ SM PLA，req ≤ΔSM PLA，avai ，
In the formula: Δ SM PLA，req For variation of stability margin under power transient in actual conditions, Δ SM PLA，avai The allowable value of stability margin under power transients specified in airworthiness terms.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. A airworthiness conformance verification method for an aircraft engine power transient, comprising the following operational steps:
s1: determining a limit condition of the influence of power transient on the stability margin in the working process of the aeroengine;
s2: obtaining an analysis program capable of simulating a stability margin change rule under the power transient of the aircraft engine;
s3: performing transient simulation on the aircraft engine in the power transient process;
s4: analyzing the change rule of the stability margin of the aero-engine along with time in the power transient simulation process in the step S3, and determining the working moment of the limit value of the stability margin and the flow of the aero-engine at the moment; and (5) according to the limit condition of the influence of the power transient on the stability margin in the step S1, simultaneously analyzing the change rule of the stability margin calculated in the step S2, and determining the airworthiness conformity of the aero-engine under the power transient.
2. The method of claim 1, wherein the determination of limit conditions in step S1 includes the determination and comparison of surge and stall.
3. The method of verifying airworthiness of an aircraft engine power transient of claim 1, wherein the determining the basis in the limiting condition in step S1 comprises: the operating environment of the aircraft, the flight mission and the type of aircraft engine fitted, wherein,
the working environment of the aircraft comprises: altitude and mach number;
the flight mission comprises the following steps: rapid acceleration and rapid deceleration;
the aircraft engine types include: split turbofan engines, mixed-row turbofan engines, turbojet engines, turboshaft engines, and turboprop engines.
4. The airworthiness validation method for an aircraft engine power transient of claim 1, wherein in step S2, component modules required for the aircraft engine are retrieved from the library according to the aircraft-assembled aircraft engine type in step S1; and simultaneously inputting parameters of all parts of the aero-engine into the corresponding modules, wherein the parameters of all parts of the aero-engine comprise a performance map, pneumatic parameters and geometric parameters.
5. The method of claim 1, wherein in step S3, an aircraft engine power transient is determined and modeled based on the flight mission and aircraft engine type of the aircraft determined in step S1, and the parameters of the power transient are input into a dynamic module of an analysis program, thereby implementing transient simulation of the aircraft engine during the power transient.
6. The airworthiness verification method for power transient of aircraft engine according to claim 1, wherein in step S2, the method includes selecting a component module of the aircraft engine to establish a stability analysis program, and obtaining an analysis program capable of simulating a variation law of stability margin under power transient of the aircraft engine, and the method includes the following steps:
SS1, entering an MATLAB SIMULINK module layer, and building a calculation module of the core component of the aero-engine to form a User module library;
selecting a built and packaged component module for lapping according to the type of the aero-engine subjected to airworthiness conformance verification;
SS2, inputting the performance map of the component at the bottom layer of each component module, and inputting boundary condition constraint parameters at the inlet and outlet of the component module;
and SS3, establishing a component matching relation based on the type of the aero-engine, determining a common working equation of the aero-engine, inputting parameters such as mechanical shaft transmission efficiency and the like in a program solving layer, and improving program fidelity.
7. The method for verifying the airworthiness of the power transient of the aircraft engine as claimed in claim 6, wherein in the step of SS1, component modules comprise an air inlet channel, a compressor, a combustion chamber, a turbine and a tail nozzle, and a multi-stage compressor and turbine module connection is required for a double-shaft or three-shaft aircraft engine;
in the SS2 step, the boundary condition constraint parameters comprise the temperature, the pressure and the flow at the part inlet and the sectional area of the interface between the parts, and after the boundary conditions of the module are completely defined, the calling of the single part can be completed, and the part performance of the aero-engine can be simulated;
in the step of SS3, the common working equations include flow balance, pressure balance, physical speed identity and power balance.
8. The method for verifying airworthiness of an aircraft engine power transient of claim 1, wherein the step S3 of applying a stability analysis program to simulate the transient state of the aircraft engine during the power transient comprises the steps of:
a: calling a dynamic module in an aircraft engine stability analysis program, adding a rotor dynamics equation to determine the real-time matching relationship of parts, wherein the common working equation of the aircraft engine changes at the moment, the residual power caused by the change of oil supply along with time in the dynamic effect is considered, the power balance condition is not applicable any more, and the power transient process at the moment can be described as shown in the following formula:
wherein, in the formula: n is the physical rotation speed of the engine shaft, J is the moment of inertia of the rotating part, t is time, eta is the mechanical efficiency of the rotating shaft, Pow T Power supplied to the turbine, Pow acc Load, the amount of power draw required for engine accessory operation C Rotating a load for an engine compressor;
b: modeling specific parameters of a power transient according to specific operating conditions of the aircraft engine.
9. The method of claim 8, wherein the specific parameters of the modeled power transient include: a power transient type, a total duration of the power transient, a power change rate of the power transient, and an initial speed of the power transient, the power transient type including rapid acceleration and rapid deceleration.
10. The method for verifying the airworthiness of the power transient of the aircraft engine according to claim 1, wherein in step S4, the step of determining the airworthiness of the aircraft engine under the power transient comprises the following steps:
a: analyzing a change rule of the stability margin in the power transient process, and determining a limit value and a corresponding position of the stability margin in the power transient process;
b: in comparison with the limit condition of the impact of the power transient on the stability margin in step S1, the compliance under the aircraft engine power transient is determined as follows:
ΔSM PLA，req ≤ΔSM PLA，avai ，
wherein, in the formula, Delta SM PLA，req For variation of stability margin under power transient in actual conditions, Δ SM PLA，avai The allowable value of stability margin under power transients specified in airworthiness terms.
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