Aero-engine installation thrust evaluation method based on takeoff and skating data
An aero engine and engine technology, applied in geometric CAD, design optimization/simulation, etc., can solve the problems of aircraft engine calculation engine installation thrust, etc.
Active Publication Date: 2020-07-07
AIR FORCE UNIV PLA
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Problems solved by technology
[0004]
The technical problem to be solved by the present invention is to provide a method for evaluating the installation thrust of an aeroengine based on take-off and run data for the lack of sufficient cross-section parameters of the aircraft engine to calculate the engine installation thrust by the component method, using the reference point proposed by the invention The selection principle is used to determine the evaluation reference point of the installation thrust during the take-off and run phase, and the effective take-off and run data is screened based on the evaluation reference point, and the installed thrust of the engine is calculated by using the take-off and run data, and the thrust is allocated and converted, and finally obtained for the evaluation of engine performance degradation Installed thrust data for the takeoff roll
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[0046] The invention provides a method for evaluating the installation thrust of an aero-engine based on take-off and run data. The proposed reference point selection principle is used to determine the evaluation reference point of the installation thrust in the take-off and run stage, and effective data is screened based on the evaluation reference point. The data is used to calculate the installed thrust of the engine and perform thrust distribution and conversion, and finally obtain the installed thrust data for take-off roll for engine performance degradation evaluation. Compared with the prior art, the invention can quantitatively evaluate the installation thrust of the engine in the take-off and rolling state under the condition of unknown engine component characteristics and section parameters, has the advantages of practicality and convenience, and can provide technical support for engine thrust decline evaluation.
[0047] The present invention adopts following technic...
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The invention discloses an aero-engine installation thrust evaluation method based on takeoff and taxiing data. The method comprises the steps of determining a fixed state point for evaluating the installation thrust in the takeoff and taxiing stage by utilizing the proposed reference point selection principle, screening effective data based on fixed state point conditions, calculating the installation thrust of the engine by utilizing the takeoff and taxiing data, carrying out thrust distribution and conversion, and finally obtaining the takeoff and taxiing installation thrust data for evaluating the performance degradation of the engine. Compared with the prior art, the method has the advantages that the mounting thrust of the engine in the takeoff and skating state can be quantitativelyevaluated under the condition of unknown engine part characteristics and section parameters, the method is practical and convenient, and technical support can be provided for thrust recession evaluation of the engine.
Description
technical field [0001] The invention relates to the technical field of aero-engine thrust evaluation, in particular to an installation thrust evaluation method of an aero-engine in the take-off and rolling phase. Background technique [0002] With the increase of the service time of the aero-engine, the decline of the efficiency of each component leads to a decline in the performance of the engine, which is mainly manifested in the decrease of thrust and the increase of fuel consumption rate under the same working condition, which directly affects the performance, safety and economy of the aircraft. Accurate evaluation of engine installation thrust has important guiding significance for engine performance analysis and fleet performance ranking. Performance evaluation is to calculate and evaluate the performance of aero-engines through technical means, which can be divided into two categories: absolute performance evaluation and service performance evaluation. [0003] The a...
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Login to View More IPC IPC(8): G06F30/20G06F30/15
CPCY02T90/00
Inventor 陈卫程礼郑铁军陈煊王志多张小博谢武赵彪
Owner AIR FORCE UNIV PLA