Construction method of gas compressor/turbine transition runner with support plate

A technology of transition flow channel and construction method, which is applied in special data processing applications, instruments, electrical digital data processing, etc., and can solve the problems of large loss and poor practicability of rapidly expanding flow channels

Inactive Publication Date: 2019-09-06
DALIAN UNIV OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] In order to overcome the shortcomings of poor practicability of the existing methods, accurately describe the upper and lower wall profiles of the transition channel, and avoid excessive loss of the designed rapidly expanding channel, the present invention proposes a compressor with a support plate. Th

Method used

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  • Construction method of gas compressor/turbine transition runner with support plate
  • Construction method of gas compressor/turbine transition runner with support plate
  • Construction method of gas compressor/turbine transition runner with support plate

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Embodiment Construction

[0061] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings and technical solutions.

[0062] The specific steps of the three-dimensional construction method of the compressor / turbine transition channel with a support plate of the present invention are as follows:

[0063] In this example, the initial compressor runner constraints are given in the following table:

[0064]

[0065] According to the given inlet and outlet coordinates of the expansion surface of the flow channel, the working medium in the flow channel is ideal air with a density of 1.044kg / m 3 , the flow velocity is 204m / s, and the viscosity coefficient is 1.7e -5 , Re takes 3e 5 , according to formula (1), the reference curvature radius r of the transition arc between the inlet and outlet of the runner expansion surface profile line can be obtained as 1.25cm, m 1 , m 2 Respectively: 10, 24. Combined with the coordinates of the endp...

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Abstract

The invention provides a construction method of a gas compressor/turbine transition runner with a support plate. The construction method includes the steps: determining inlet and outlet arcs of the transition runner expansion surface profile according to the runner inlet and outlet states, and finding out an inscribed line of a circle where the two arcs are located to serve as a straight line section of the expansion surface profile, wherein the inlet and outlet arcs and the middle straight line section jointly form the expansion surface profile of the runner; giving normal height distributionof the runner through the height of an inlet and an outlet, then solving coordinates of corresponding points on a shrinkage surface profile till convergence is achieved, and obtaining an initial shrinkage surface profile of the runner; and finally, considering the blocking effect of the support plate, calculating the blocking area of the support plate, increasing the height of the runner to compensate the blocking of the support plate, and obtaining the corrected runner shrinkage surface line. The gas compressor/turbine transition runner with the support plate solves the problems that a construction method in the prior art is poor in practicability and not suitable for a sudden expansion type runner with an overlarge expansion angle.

Description

technical field [0001] The invention relates to a method for constructing a compressor / turbine transition flow channel, in particular to a two-dimensional / three-dimensional construction method for a compressor / turbine transition channel with a support plate. Background technique [0002] The compressor transition channel is an important static part connecting the low-pressure compressor and the high-pressure compressor on the aero-engine. It is responsible for transporting the compressed air of the former to the latter for further compression; the turbine transition channel is located at the high and low pressure of the aero-engine. Between the turbines, it also acts as a transition, which can transition the high-pressure turbine air flow to the low-pressure turbine. In order to reduce the weight of the transition flow channel and its surrounding accessories, and also shorten the length of the high and low pressure rotors, thereby reducing the strength load of the rotor syst...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/17
Inventor 杨金广吴楠刘源泉刘艳张敏
Owner DALIAN UNIV OF TECH
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