CN109460628B - Flow matching evaluation method for joint work of air inlet channel and engine - Google Patents
Flow matching evaluation method for joint work of air inlet channel and engine Download PDFInfo
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- CN109460628B CN109460628B CN201811535933.5A CN201811535933A CN109460628B CN 109460628 B CN109460628 B CN 109460628B CN 201811535933 A CN201811535933 A CN 201811535933A CN 109460628 B CN109460628 B CN 109460628B
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Abstract
The invention belongs to the technical field of integrated design of aircraft/engines, and relates to a flow matching evaluation method for the joint work of an air inlet channel and an engine. According to the simulation calculation method, firstly, flow coefficient-total pressure recovery coefficient characteristic data of an air inlet channel are obtained through an air blowing test, engine component characteristic data are obtained through an engine component test, and then the flow coefficient-total pressure recovery coefficient characteristic of the air inlet channel is coupled into an engine performance residual calculation model, so that the simulation calculation method is simple to realize and quick to calculate. The flow matching condition of the air inlet channel and the engine can be accurately simulated when the air inlet channel and the engine work together, and the calculation result can provide corresponding basis for performance matching evaluation of the air inlet system and the engine.
Description
Technical Field
The invention belongs to the technical field of integrated design of aircraft/engines, and relates to a flow matching evaluation method for the joint work of an air inlet channel and an engine.
Background
At present, the commonly used method for evaluating the influence of an air inlet channel on the performance of an aeroengine is as follows: and selecting corresponding intake total pressure recovery coefficients under different flight Ma numbers according to an empirical formula, and correcting the total pressure parameters of the inlet of the engine so as to calculate the performance of the engine once. From these assumptions, it can be derived that: the total pressure loss in the inlet is only related to the flight mach number. However, in practice, especially in supersonic flight, the total pressure loss of the air inlet channel affects the flow rate of the engine working together, but the required flow rate of the engine also affects the total pressure loss of the air inlet channel, so that iterative calculation is needed to match the flow rate of the air inlet channel with the flow rate of the engine. Therefore, in the process of evaluating the matching of the air inlet and the engine performance, the flow coefficient characteristic of the air inlet is required to be coupled into an engine performance calculation program, and a corresponding evaluation basis is provided for the matching of the air inlet and the engine performance, which is also an important aspect of the integrated design of the aircraft and the engine.
Disclosure of Invention
The purpose of the invention is that: the flow matching evaluation method for the joint work of the air inlet and the engine can evaluate the flow matching condition of the joint work of the air inlet and the engine rapidly and accurately.
In order to solve the technical problem, the technical scheme of the invention is as follows:
a flow matching evaluation method for the joint work of an air inlet and an engine establishes an iterative evaluation model for the flow matching of the air inlet and the engine based on the flow balance of the outlet of the air inlet and the inlet of a fan.
The method is characterized in that: the flow matching evaluation method for the joint work of the air inlet channel and the engine comprises the following steps:
step one, obtaining the flow rate-total pressure recovery coefficient characteristic of an air inlet channel and the characteristic of an engine part;
step two, establishing an air inlet channel-engine flow matching iterative calculation model;
and thirdly, calculating matched flow of the joint work of the air inlet channel and the engine according to specific flight conditions, and calculating performance data of the air inlet channel and the engine.
The first step is specifically as follows:
according to an air inlet channel wind tunnel blowing test and an engine part test, respectively obtaining the flow coefficient-total pressure recovery coefficient characteristic of an air inlet channel, the flow-supercharging ratio characteristic and the flow-efficiency characteristic of an engine compressor; turbine flow-to-pressure ratio characteristics, and flow-to-efficiency characteristics of the engine.
The second step is specifically as follows:
taking the air inlet channel as a part of the engine, performing thermodynamic cycle calculation, and establishing a joint working equation set for evaluating the flow balance and the energy balance of the engine;
and calculating the beta value of the characteristic diagram of the total pressure recovery coefficient of the air inlet channel increased by the iteration variable of the engine joint working equation set, and increasing the flow balance equation of the outlet of the air inlet channel and the inlet of the fan by the balance equation.
The third step is specifically as follows:
and (3) according to specific flight conditions, solving a nonlinear equation set by combining the air inlet channel-engine joint operation equation set established in the step two, and obtaining matched flow of joint operation of the air inlet channel and the engine and performance data of the air inlet channel and the engine.
The specific flight conditions are as follows: number of flight Ma, atmospheric temperature, altitude, engine status.
The beneficial effects of the invention are as follows: according to the flow matching evaluation method for the joint work of the air inlet and the engine, the flow matching condition of the air inlet and the engine is fully considered when the performance of the aeroengine is evaluated, the engine installation performance taking the total pressure recovery coefficient of the air inlet into consideration can be more accurately simulated, the calculation result can provide corresponding basis for evaluating the matching condition of the air inlet and the engine, the installation performance of the air inlet and the engine after installation is ensured to a greater extent, and the risk cost which cannot meet the performance requirement of an airplane due to poor matching of the air inlet and the engine is reduced in the initial stage of design.
Drawings
FIG. 1 is a flow chart of a method of flow matching assessment of an air intake co-operating with an engine according to the present invention;
FIG. 2 is a graph showing the total pressure recovery coefficient of an air inlet after a certain Pitot type air inlet and a certain split large bypass ratio turbofan engine are matched in a co-operation manner;
FIG. 3 shows the flow rate of a pitot type inlet duct matched with a split large bypass ratio turbofan engine;
FIG. 4 shows the engine thrust after a Pitot type air inlet and a split large bypass ratio turbofan engine work together and match.
Detailed Description
The invention is further illustrated by the following examples in conjunction with the accompanying drawings:
the flow matching evaluation method for the joint work of the air inlet and the engine couples the flow-total pressure recovery coefficient characteristic of the air inlet with the joint work characteristic of the engine, adds an air inlet and the flow balance equation of the engine in the joint work equation confirmed by the flow balance and the energy balance among engine parts (an air compressor, a combustion chamber, a turbine and the like), solves a linear equation set together, and can obtain the performance of the engine meeting the matching of the flow of the air inlet and the engine.
The flow of the method of the invention is shown in figure 1 and comprises the following steps:
step one: obtaining the flow-total pressure recovery coefficient characteristic of an air inlet passage and the characteristic of an engine part
According to an air inlet channel wind tunnel blowing test and an engine part test, respectively obtaining:
a. flow coefficient-total pressure recovery coefficient characteristics of the air inlet channel under different Mach numbers; for the convenience of calculation, the intake passage characteristic map is first processed. When the air inlet is in subcritical state and supercritical state, the large section of the total pressure recovery characteristic of the air inlet is in a straight section, and a large error is caused when a common interpolation method is used, so that the total pressure recovery characteristic diagram of the air inlet is converted into a beta characteristic diagram. The β characteristic map is an equal β line in which an upper boundary line is defined as β=1, a lower boundary line is defined as β=0, and equal pitches are generated in the middle.
b. Flow-to-boost ratio characteristics, flow-to-efficiency characteristics of an engine compressor; turbine flow-to-pressure ratio characteristics, flow-to-efficiency characteristics of the engine;
step two: establishing an iterative calculation model for matching air inlet channel and engine flow
The intake duct is used as a part of the engine to perform thermodynamic cycle calculation, and a common working equation set indicating the flow balance and the energy balance of the engine is established. Because of the addition of the intake port component, the iteration variable and the error variable of the engine joint operation equation are respectively increased by one. Taking the two types of engines most common at present as examples, the following are respectively described:
first category: taking a biaxial split turbofan engine as an example, assuming that the engine thrust control parameter is the low pressure shaft speed, the engine thermodynamic cycle calculates the assumed unknowns to increase to 8, respectively: the total pressure recovery coefficient characteristic diagram beta value of the air inlet channel, the fan supercharging ratio, the bypass ratio, the high-pressure shaft rotating speed, the high-pressure compressor supercharging ratio, the combustion chamber outlet temperature, the high-pressure turbine folding flow and the low-pressure turbine folding flow. Meanwhile, according to the common working condition of engine parts, the mixed exhaust turbofan engine must satisfy the following 8 balance equations when working at non-design points:
inlet outlet-fan inlet flow balance
Fan content outlet-high pressure compressor inlet flow balance
Combustor outlet-high pressure turbine inlet flow balancing
High pressure compressor-high pressure turbine work balance
High pressure turbine outlet-low pressure turbine inlet flow balancing
Fan-low pressure turbine work balance
Flow balance of fan outer culvert outlet-outer culvert spray pipe
Low pressure turbine outlet-content jet flow balancing
The second category: taking a double-shaft mixed exhaust turbofan engine as an example, assuming that the engine thrust control parameter is the low-pressure shaft rotating speed, the engine thermodynamic cycle calculates that the assumed unknowns are increased to 8, and the unknown values are respectively: the total pressure recovery coefficient characteristic diagram beta value of the air inlet channel, the fan supercharging ratio, the bypass ratio, the high-pressure shaft rotating speed, the high-pressure compressor supercharging ratio, the combustion chamber outlet temperature, the high-pressure turbine folding flow and the low-pressure turbine folding flow. Meanwhile, according to the common working condition of engine parts, the mixed exhaust turbofan engine must satisfy the following 8 balance equations when working at non-design points:
inlet outlet-fan inlet flow balance
Fan content outlet-high pressure compressor inlet flow balance
Combustor outlet-high pressure turbine inlet flow balancing
High pressure compressor-high pressure turbine work balance
High pressure turbine outlet-low pressure turbine inlet flow balancing
Fan-low pressure turbine work balance
Static pressure balancing of mixing chamber blended air flow
Flow balancing of mixing chamber outlet/afterburner outlet-tail nozzle
Step three: calculating matched flow of the joint work of the air inlet and the engine according to specific flight conditions and performance data of the air inlet and the engine
According to specific flight conditions (flight Ma number, atmospheric temperature and the like), the non-linear equation set is solved by combining the air inlet channel-engine joint operation equation set established in the second step to obtain the engine performance considering the total pressure recovery coefficient of the air inlet channel, including engine flow, thrust, fuel consumption and the like, and the total pressure recovery coefficient and flow coefficient of the air inlet channel can also be obtained, so that the resistance of the air inlet channel is calculated
In the example, in the second step, eight sets of common working equations are set up for the first-class engine and a certain Pitot subsonic inlet channel;
in the third step, matching flow of the joint work of the air inlet and the engine and performance data of the air inlet and the engine are calculated according to specific flight conditions:
and respectively selecting the height ranges of 0km, 5km and 11km, and calculating the Mach number ranges of 0-0.5, 0.2-0.7 and 0.3-0.9 to obtain the total pressure recovery coefficient of the air inlet channel, the engine flow, the thrust and the like after being matched with the air inlet channel, wherein the calculation results are shown in figures 2, 3 and 4.
According to the calculation result, the total pressure recovery coefficient of the air inlet channel is reduced sharply under the low Mach number flight condition, and the calculation result accords with the physical phenomenon because the lip airflow of the air inlet channel is separated. The method has engineering application prospect. The calculation result can provide corresponding basis for evaluating the matching condition of the air inlet channel and the engine, so that the installed performance of the air inlet channel and the engine is ensured to a greater extent, and the risk cost which does not meet the performance requirement of the aircraft due to poor matching of the air inlet channel and the engine is reduced in the initial design stage.
Claims (3)
1. A flow matching evaluation method for the joint work of an air inlet channel and an engine is characterized in that: the flow matching evaluation method is characterized in that an inlet channel-engine flow matching iterative evaluation model is established based on the condition of inlet channel outlet-fan inlet flow balance; the flow matching evaluation method is used for a double-shaft split turbofan engine or a double-shaft mixed turbofan engine;
the flow matching evaluation method for the joint work of the air inlet channel and the engine comprises the following steps:
step one, obtaining the flow rate-total pressure recovery coefficient characteristic of an air inlet channel and the characteristic of an engine part;
step two, establishing an air inlet channel-engine flow matching iterative calculation model;
taking the air inlet channel as a part of the engine, performing thermodynamic cycle calculation, and establishing a joint working equation set for evaluating the flow balance and the energy balance of the engine;
the assumed unknowns are respectively: the total pressure recovery coefficient characteristic diagram beta value of the air inlet channel, the fan supercharging ratio, the bypass ratio, the high-pressure shaft rotating speed, the high-pressure compressor supercharging ratio, the combustion chamber outlet temperature, the high-pressure turbine folding flow and the low-pressure turbine folding flow; the balance equation increases the flow balance equation of the inlet channel outlet and the fan inlet;
and thirdly, according to specific flight conditions, solving a nonlinear equation set by combining the air inlet channel-engine joint operation equation set established in the second step to obtain matched flow of joint operation of the air inlet channel and the engine and performance data of the air inlet channel and the engine.
2. The method for estimating flow matching between an intake duct and an engine of claim 1, wherein: the first step is specifically as follows:
according to an air inlet channel wind tunnel blowing test and an engine part test, respectively obtaining the flow coefficient-total pressure recovery coefficient characteristic of an air inlet channel, the flow-supercharging ratio characteristic and the flow-efficiency characteristic of an engine compressor; turbine flow-to-pressure ratio characteristics, and flow-to-efficiency characteristics of the engine.
3. The method for estimating flow matching between an intake duct and an engine of claim 1, wherein: the specific flight conditions are as follows: number of flight Ma, atmospheric temperature, altitude, engine status.
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| CN112507476B (en) * | 2020-11-03 | 2024-05-24 | 南京航空航天大学 | Integrated modeling method for variable geometry air inlet channel and engine |
| CN112412632B (en) * | 2020-11-19 | 2022-03-04 | 中国航发沈阳发动机研究所 | Aero-engine surge oil cutting method and system based on inlet flow matching |
| CN112784380B (en) * | 2021-03-23 | 2022-02-22 | 北京清软创想信息技术有限责任公司 | Method and system for optimally designing external-internal content pressure ratio |
| CN113945385B (en) * | 2021-09-21 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Model system for jet engine and air inlet channel ground bench combined test |
| CN118408673B (en) * | 2024-06-28 | 2024-09-03 | 中国航发四川燃气涡轮研究院 | Method and system for correcting total pressure of inlet of air compressor based on intermediate casing loss model |
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