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One-dimensional high-low-pressure turbine transition flow channel optimization design method

A technology of transition flow channel and optimized design, applied in computing, special data processing applications, instruments, etc., can solve problems such as poor practicability

Inactive Publication Date: 2015-04-22
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0006] In order to overcome the shortcomings of poor practicability of the existing methods, the present invention provides a one-dimensional optimal design method for high and low pressure turbine transition passages

Method used

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  • One-dimensional high-low-pressure turbine transition flow channel optimization design method
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  • One-dimensional high-low-pressure turbine transition flow channel optimization design method

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Embodiment Construction

[0037] refer to Figure 1-2 . The specific steps of the one-dimensional optimal design method for the high-low pressure turbine transition channel of the present invention are as follows:

[0038] According to the known size and geometry of the inlet and outlet of the runner, the initial constraints given in this example are as follows:

[0039]

[0040] Then calculate θ according to formula (1) c and determine L m . Calculate the equivalent expansion angle θ according to formula 1 c =17.6895°, the flow channel is a rapidly expanding flow channel.

[0041] θ c is the equivalent cone expansion angle; L m is the meridional length of the transition channel; A 1 is the normal area of ​​the transition channel inlet; A 2 is the normal area of ​​the outlet of the transition channel.

[0042] θ c = 2 arctan ( A 2 ...

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Abstract

The invention discloses a one-dimensional high-low-pressure turbine transition flow channel optimization design method. The method aims to solve the technical problem that an existing method is poor in practicability. According to the technical scheme, an end wall profile equation meeting the transition flow channel geometric constraint is built by the adoption of a Bezier curve; the disturbance quantity meeting the orthogonal polynomials is generated afterwards, and correction is conducted on the generated extremely large disturbance quantity to prevent deformation of a disturbed flow channel; a new high-low-pressure turbine transition flow channel profile equation is generated based on the existing transition flow channel geometric profile equation; a flow field performance parameter is solved through a flow control equation on the high-low-pressure turbine transition flow channel center line; a total pressure recovery coefficient serves as an optimization objective function, and a complex method is adopted till an iteration result meets the accuracy requirement. According to the method, the high-low-pressure turbine transition flow channel profile equation is built based on the Bezier curve to optimize the high-low-pressure turbine transition flow channel, the defect that the existing method is not suitable for an urgently-expanded flow channel with the larger expansion angle is overcome, and practicability is high.

Description

technical field [0001] The invention relates to a design method for a high-low pressure turbine transition channel, in particular to a one-dimensional optimization design method for a high-low pressure turbine transition channel. Background technique [0002] The turbine transition channel connecting the high-pressure turbine and the low-pressure turbine is an important part of the large bypass gas turbine engine, and the air flow in the turbine transition channel needs to undergo a deceleration and diffusion process. According to the classic diffuser theory, the air flow is easily separated in the diffuser channel. In order to avoid the flow loss caused by the separation, the axial length of the channel must be increased to reduce the degree of diffusion, and the increase in the axial length will inevitably bring about the increase in the weight and cost of the turbine. Increase. [0003] For a long time, the design of the turbine transition passage has not received enough...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
Inventor 吴虎杨金广侯朝山刘昭威
Owner NORTHWESTERN POLYTECHNICAL UNIV
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