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Method for obtaining control value of temperature behind turbine of aviation engine at high altitude and high speed

An aero-engine and temperature control technology, which is applied in the cooling of the engine, engine components, machines/engines, etc., and can solve the problems of unsatisfactory results and huge development costs.

Inactive Publication Date: 2018-08-28
CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD
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Problems solved by technology

Before the empirical formula is obtained, it is necessary to spend a huge amount of research and development costs and bear the risks brought about by the experiment.
In addition, the value of this parameter calculated according to the forward model is often unsatisfactory. In general, the difference between the calculated value and the real value can reach 40°C

Method used

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  • Method for obtaining control value of temperature behind turbine of aviation engine at high altitude and high speed
  • Method for obtaining control value of temperature behind turbine of aviation engine at high altitude and high speed
  • Method for obtaining control value of temperature behind turbine of aviation engine at high altitude and high speed

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Embodiment Construction

[0059] The present invention will be described in detail below in conjunction with the examples.

[0060] The present invention provides a method for obtaining a temperature control value after a turbine of an aero-engine at high altitude and high speed, comprising the following steps:

[0061] 1) Select several parameters most relevant to engine efficiency from the engine history book.

[0062] There are more than 60 parameters recorded in this parameter of the engine history, these parameters include some performance parameters of the engine in various stable working states and transition states, such as starting time, temperature after the turbine when starting, fuel auxiliary oil circuit pressure, high and low pressure Speed ​​conversion value, turbine temperature conversion value, engine vibration value, acceleration and deceleration time, turbine drop pressure ratio, fuel oil temperature value, air pressure value after compressor, lubricating oil pressure value, tail noz...

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Abstract

The invention relates to a method for obtaining control value of temperature behind a turbine of an aviation engine at high altitude and high speed. The method comprises the following steps of (1) screening several parameters which are mostly related with the engine efficiency from an engine logbook; (2) on the basis of using the known control values of the temperature behind the turbines of morethan hundreds of engines at high altitude and high speed as a training set, establishing a nervous network, using the selected parameters as input nodes, and using the control value of the temperaturebehind the turbine as the target value to train; after training, obtaining a nervous network model for calculating the control value of the temperature behind the turbine of the aviation engine at high altitude and high speed.

Description

technical field [0001] The invention relates to a method for acquiring a temperature control value after a turbine of an aero-engine at high altitude and high speed, and belongs to the technical field of aero-engines. Background technique [0002] In the case of high altitude and high speed, the aeroengine will ablate the turbine blades in order to prevent the temperature before the turbine from exceeding the limit value, so it is very important to obtain the control value of the temperature after the turbine. Due to the technical blockade imposed by foreign countries on our country, the empirical formula of the control value of the temperature after the turbine of the aero-engine is kept secret from our country, and different engines have different empirical formulas. How to obtain the control value is very important to the development of my country's aero-engine technology. At present, the commonly used method in China to obtain the control value of the post-turbine tempe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/00F02C7/12F01D21/00F01D21/12F01D25/08F02C9/00G06Q50/04
CPCY02P90/30F02C7/12F01D21/003F01D21/12F01D25/08F02C7/00F02C9/00G06Q50/04
Inventor 郭洪尧胡兰田雷徐赋明
Owner CHINA HANGFA GUIZHOU LIYANG AVIATION POWER CO LTD
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