Method for determining upper limit of environmental temperature in nacelle

A technology of upper temperature limit and ambient temperature, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as unsuitable for fast engineering calculation, long calculation cycle, and complexity, and achieve easy implementation, high precision, and method Simple and convenient effect

Active Publication Date: 2015-07-01
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

In order to predict the ambient temperature of the nacelle under this state, the method of numerical simulation is usually used to obtain it, but because the implementation of the numerical simulation method of the heat transfer process of the nacelle is too complicated and the calculation period is long, it is not suitable for rapid engineering calculations

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  • Method for determining upper limit of environmental temperature in nacelle
  • Method for determining upper limit of environmental temperature in nacelle
  • Method for determining upper limit of environmental temperature in nacelle

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Embodiment 1

[0037] The present invention determines the calculating method of ambient temperature upper limit in aircraft nacelle, its flow process is as follows figure 1 shown, including the following steps:

[0038] Step 1: Obtain the average temperature of the engine surface

[0039] like figure 2 As shown, according to the core components of the engine, the engine is divided into four sections along the axial direction. The surface temperature of the engine casing is obtained from the engine test, and the average surface temperature T of each section of the casing is obtained respectively. n ,like image 3 As shown, the temperature of each section is expanded as follows: Compressor section T 1 =316K, combustion chamber section T 2 =361K, turbine section T 3 =366K, nozzle section T 4 =373K; take the maximum value T w =T 4 = 373K;

[0040] Step 2: Determine the temperature extremes of the aircraft operating environment

[0041] According to the actual working conditions of th...

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Abstract

The invention belongs to a design technology for an airplane accessory, and relates to a method for determining upper limit of environmental temperature in a nacelle. The method comprises the following steps of: acquiring temperature on the surface of an engine crankcase through experiments; determining atmospheric environmental temperature for working of an airplane; measuring sectional radiuses of an engine and the nacelle according to data models or real objects of the engine and the nacelle; and finally, performing numerical fitting calibration to obtain an empirical formula according to a thermodynamic principle, aerodynamics and working characteristics of a ventilating and cooling system of the nacelle of the airplane by combining actual test and engineering experience and calculating to obtain the upper limit of the environmental temperature in the nacelle. The method has the advantages of easiness, convenience, easiness for implementation, high accuracy and capability of meeting actual engineering requirements.

Description

technical field [0001] The invention belongs to the aircraft accessory design technology and relates to a method for determining the upper limit of the ambient temperature in the aircraft nacelle. Background technique [0002] The engine is one of the main heat-generating components of an aircraft, and there are usually many system components and working accessories around it, including some electronic components that are sensitive to temperature. This requires considering the influence of the high temperature environment caused by the engine, estimating the working ambient temperature of some engine accessories in the nacelle, and then calculating the upper limit of the nacelle ambient temperature as the design index of the engine accessories. How to predict the temperature field of the concerned parts more accurately, carry out targeted ventilation design and provide design input for other systems has become the focus and difficulty of ventilation and cooling system design...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F19/00
Inventor 吴宇钟剑龙吕其明
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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