CN-115270337-B - Method for evaluating overall performance of aeroengine

Abstract

The application belongs to the technical field of overall performance evaluation of aero-engines, and particularly relates to an overall performance evaluation method of an aero-engine, which is characterized in that on the basis of calculating pump power consumption, an aero-engine power balance equation is corrected by using the pump power consumption, and the overall performance of the aero-engine is evaluated by using the corrected aero-engine power balance equation, wherein the pump power consumption is fully considered, and the obtained evaluation result has higher reliability through experiments and simulation verification.

Inventors

• YAN WEI
• ZHAO HONGJIAO
• LI JUN
• ZHAO YIZHEN
• YANG SHOUHUI
• LI RUI
• HAN WENJUN
• YANG FAN
• ZHAO PUYANG

Assignees

• 中国航发沈阳发动机研究所

Dates

Publication Date

20260505

Application Date

20220729

Claims (7)

1. 1. A method for evaluating overall performance of an aircraft engine, comprising: Calculating pump power consumption; correcting an aeroengine power balance equation by pump power consumption; estimating the overall performance of the aero-engine by using a corrected aero-engine power balance equation; The power balance equation of the aero-engine is corrected by pumping power consumption, and specifically comprises the following steps: ; Wherein, the Power is consumed for the compressor; is the mechanical efficiency of the compressor; is pumping power consumption; losing power for other turbines; Generating power for the turbine; Or alternatively The power balance equation of the aero-engine is corrected by pumping power consumption, and specifically comprises the following steps: ; Wherein, the Power is consumed for the compressor; is the mechanical efficiency of the compressor; losing power for other turbines; The ratio of pump power consumption to turbine power; Generating power for the turbine; the calculation of the pump power consumption is specifically as follows: ; Wherein, the Is pumping power consumption; The amount of bleed air for entering the rotor blade; Is the rotational speed of the turbine; Is the correlation coefficient of turbine geometric parameters and the front-back pressure ratio of the pre-swirl nozzle.
2. 2. The method for evaluating overall performance of an aircraft engine according to claim 1, wherein, The calculation of the pump power consumption is specifically as follows: ; ; Wherein, the Is pumping power consumption; is the turbine disk torque; Is the turbine angular velocity; The amount of bleed air for entering the rotor blade; Circumferential velocity at the rotor blade root for bleed air; radius of the rotor blade root; the circumferential speed of the bleed air in the pre-swirl nozzle; Is the radius of the location of the pre-swirl nozzle.
3. 3. The method for evaluating the overall performance of an aircraft engine according to claim 2, wherein, ; Wherein, the The ratio between the bleed air quantity entering the rotor blade and the inlet air quantity of the compressor is in the range of 4% -7%; Is the air flow rate of the inlet of the compressor.
4. 4. The method for evaluating the overall performance of an aircraft engine according to claim 2, wherein, ; ; ; ; ; Wherein, the A velocity at the outlet of the pre-swirl nozzle for bleed air; The air flow angle of the outlet of the pre-swirl nozzle; Is the velocity factor at the exit of the pre-swirl nozzle; Is the specific heat ratio of the bleed air; Is a gas constant; the temperature of the bleed air at the outlet of the pre-swirl nozzle; as a function of the flow of bleed air at the outlet of the pre-swirl nozzle; is the flow of bleed air at the outlet of the pre-swirl nozzle; is the pressure of the bleed air at the outlet of the pre-swirl nozzle; is the area of the outlet of the pre-swirl nozzle; The ratio of the air-entraining amount at the pre-swirl nozzle to the air flow at the inlet of the air compressor is in the range of 4% -7%; Is the air flow rate of the inlet of the compressor.
5. 5. The method for evaluating the overall performance of an aircraft engine according to claim 2, wherein, ; ; Wherein, the Is the rotational speed of the turbine.
6. 6. The method for evaluating overall performance of an aircraft engine according to claim 1, wherein, ; Wherein, the Enthalpy for the compressor outlet; The air flow is the inlet air flow of the compressor; enthalpy of the bleed air in the middle of the compressor; The middle bleed air amount of the air compressor; Is the enthalpy of the compressor inlet.
7. 7. The method for evaluating the overall performance of an aircraft engine according to claim 1, wherein, ; Wherein, the Enthalpy for turbine inlet; Inlet airflow for the turbine; Is the enthalpy of the turbine outlet.

Description

Method for evaluating overall performance of aeroengine Technical Field The application belongs to the technical field of overall performance evaluation of aeroengines, and particularly relates to an overall performance evaluation method of an aeroengine. Background In an aeroengine, a turbine works on a compressor, and in order to cool turbine rotor blades, a bleed air system is designed, as shown in fig. 1, wherein bleed air flows from the compressor, flows from a pre-swirl nozzle 3, flows along the radial direction of a turbine disc 2, flows into the rotor blades 1 from the root, and cools the rotor blades 1. In bleed air systems, when bleed air flows radially along the turbine disc 2, turbine work losses are generated, which losses are generated by the centrifugal pump effect of the turbine disc, which are pump work losses, which are not fully considered in the current evaluation of the overall performance of the aircraft engine, and the evaluation results are not reliable enough. The present application has been made in view of the above-described technical drawbacks. It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present patent application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application. Disclosure of Invention It is an object of the present application to provide a method for evaluating the overall performance of an aircraft engine that overcomes or alleviates the technical drawbacks of at least one aspect known to exist. The technical scheme of the application is as follows: An aircraft engine overall performance assessment method, comprising: Calculating pump power consumption; correcting an aeroengine power balance equation by pump power consumption; and evaluating the overall performance of the aero-engine by using the corrected aero-engine power balance equation. According to at least one embodiment of the present application, in the method for evaluating overall performance of an aeroengine, the calculating pump power consumption specifically includes: ; ; Wherein, the Is pumping power consumption; is the turbine disk torque; Is the turbine angular velocity; The amount of bleed air for entering the rotor blade; Circumferential velocity at the rotor blade root for bleed air; radius of the rotor blade root; the circumferential speed of the bleed air in the pre-swirl nozzle; Is the radius of the location of the pre-swirl nozzle. According to at least one embodiment of the present application, in the above-described method for evaluating overall performance of an aircraft engine,; Wherein, the The ratio between the bleed air quantity entering the rotor blade and the inlet air quantity of the compressor is in the range of 4% -7%; Is the air flow rate of the inlet of the compressor. According to at least one embodiment of the present application, in the above-described method for evaluating overall performance of an aircraft engine,; ; ; ; ; Wherein, the A velocity at the outlet of the pre-swirl nozzle for bleed air; The air flow angle of the outlet of the pre-swirl nozzle; Is the velocity factor at the exit of the pre-swirl nozzle; Is the specific heat ratio of the bleed air; Is a gas constant; the temperature of the bleed air at the outlet of the pre-swirl nozzle; as a function of the flow of bleed air at the outlet of the pre-swirl nozzle; is the flow of bleed air at the outlet of the pre-swirl nozzle; is the pressure of the bleed air at the outlet of the pre-swirl nozzle; is the area of the outlet of the pre-swirl nozzle; The ratio of the air-entraining amount at the pre-swirl nozzle to the air flow at the inlet of the air compressor is in the range of 4% -7%; Is the air flow rate of the inlet of the compressor. According to at least one embodiment of the present application, in the above-described method for evaluating overall performance of an aircraft engine,; ; Wherein, the Is the rotational speed of the turbine. According to at least one embodiment of the present application, in the method for evaluating overall performance of an aeroengine, the calculating pump power consumption specifically includes: ; Wherein, the Is pumping power consumption; The amount of bleed air for entering the rotor blade; Is the rotational speed of the turbine; Is the correlation coefficient of turbine geometric parameters and the front-back pressure ratio of the pre-swirl nozzle. According to at least one embodiment of the present application, in the method for evaluating overall performance of an aero-engine, the correction of the power balance equation of the aero-engine by pump power consumption is specifically as follows: ; Wherein, the Power is consumed for the com