A design method of return chamber-spoiler type processing casing of marine gas turbine compressor

A gas turbine and casing processing technology, applied in design optimization/simulation, etc., to achieve the effects of shortening the design process, improving surge margin indicators, and reducing resource and time consumption

Active Publication Date: 2021-12-17
中国船舶重工集团公司第七0三研究所
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Problems solved by technology

[0004] The object of the present invention is to provide a design method for a ship gas turbine compressor return cavity-spoiler type processing casing that solves the design problem of the ship gas turbine compressor return cavity-spoiler type processing casing

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  • A design method of return chamber-spoiler type processing casing of marine gas turbine compressor
  • A design method of return chamber-spoiler type processing casing of marine gas turbine compressor
  • A design method of return chamber-spoiler type processing casing of marine gas turbine compressor

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Embodiment Construction

[0032] The present invention is described in more detail below in conjunction with accompanying drawing example:

[0033] to combine figure 1 , Figure 2a , Figure 2b , Figure 2c , image 3 According to the present invention, a specific embodiment of the design method of the gas turbine compressor return cavity of the ship-spoiler type processing casing is realized by the following steps:

[0034] Step 1: Select the typical working conditions of the return chamber-spoiler type processing casing design. According to the aerodynamic design results of the compressor, the working condition with the smallest surge margin in each working condition is selected as the typical working condition, and the general typical working condition is selected near the low speed working condition of the compressor;

[0035] Step 2: Analyze the distribution of aerodynamic parameters of the flow field near the puff point under typical working conditions, including the relative total pressure ...

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Abstract

The purpose of the present invention is to provide a design method for the return cavity-spoiler type treatment casing of a marine gas turbine compressor, select typical working conditions according to the aerodynamic design results of the compressor, and determine the axial direction of the return flow cavity-spoiler type treatment casing The characteristic position; extract the inlet absolute airflow angle and the inlet relative airflow angle at the tip of the moving blade on the characteristic position, so as to determine the inlet radial angle and exhaust radial angle of the spoiler; select the outer diameter of the spoiler, the spoiler The three influencing factors of tape length and number of spoilers are used to design the structural scheme; again, numerical calculations are performed on different structural design schemes to determine the optimal scheme; performance analysis is performed on the optimal scheme under design conditions to judge the Whether the performance of the design point of the scheme is up to standard. The present invention is not limited to the axial flow compressor of the ship gas turbine, and is also applicable to various industrial gas turbine axial flow compressors and aeroengine axial flow compressors with processing casings.

Description

technical field [0001] The invention relates to a gas turbine design method, in particular to a compressor design method. Background technique [0002] As one of the three most important core components of a marine gas turbine, the compressor's technical performance and reliability directly affect the realization of the safety and economic indicators of a marine gas turbine. The marine gas turbine shall, while ensuring the performance of the design point, pay special attention to the margin and efficient operation under low working conditions. The operating characteristics under such a wide range of variable working conditions make the stability of gas turbines in low working conditions very prominent when they are used as propulsion or power generation in ship power systems, and often become the limiting bottleneck of unit performance, which has great impact on ship gas turbine compressors The performance and stability under non-design conditions put forward higher require...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/28
Inventor 张舟王琦洪青松金鹏王廷万新超张亮
Owner 中国船舶重工集团公司第七0三研究所
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