A performance optimization method of marine gas turbine compressor based on three-dimensional flow field analysis

A technology of three-dimensional flow field and optimization method, applied in design optimization/simulation, instrumentation, geometric CAD, etc., can solve problems such as low efficiency and pressure ratio, achieve the effect of eliminating air separation, reducing time consumption, and improving thermal insulation efficiency

Active Publication Date: 2022-07-01
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

[0003] In the early 20th century, the aerodynamic design of the compressor was based on a simple one-dimensional flow, and its efficiency and pressure ratio were relatively low

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  • A performance optimization method of marine gas turbine compressor based on three-dimensional flow field analysis
  • A performance optimization method of marine gas turbine compressor based on three-dimensional flow field analysis
  • A performance optimization method of marine gas turbine compressor based on three-dimensional flow field analysis

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Embodiment Construction

[0023] The present invention will be described in more detail below in conjunction with the accompanying drawings:

[0024] combine figure 1 , a specific implementation of a performance optimization design method for a high-performance marine gas turbine compressor based on three-dimensional flow field analysis is achieved through the following steps:

[0025] Step 1: Under the condition of the compressor at the design point, select the characteristic section of the optimization calculation; usually, different relative height positions along the blade height are used as the characteristic section, generally 5 or 7 sections are selected, and the spacing between the sections is kept equal.

[0026] Step 2: Extract the main aerodynamic parameters at the characteristic cross-section positions of the blades at the inlet of the compressor at the design point, including: the relative velocity W at the inlet of the rotor blade 1 , the relative velocity of the rotor blade outlet W 2 ...

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Abstract

The purpose of the present invention is to provide a performance optimization method of marine gas turbine compressor based on three-dimensional flow field analysis. Based on the design operating point, from the first row of blades to the last row of blades, the flow field velocity of different section heights can be checked. Distribution or Mach number distribution, confirm the flow matching of the flow field, judge the attack angle range of different section heights for each blade row, determine the blade inlet airflow angle and outlet airflow angle deviation, fine-tune the blade inlet geometric angle and outlet geometric angle, Complete the optimization adjustment; for the separation of the end zone, the end bending technology is appropriately adopted in the process of static blade modeling to optimize the design. The invention can predict the specific part of the separation flow, adjust the blade shape to eliminate the separation or reduce the separation area, so as to achieve the effect of improving the efficiency and increasing the stall margin of the compressor.

Description

technical field [0001] The invention relates to a method for optimizing the performance of a gas turbine, in particular to a method for optimizing the performance of a compressor. Background technique [0002] Ship high-power gas turbine is the key and core equipment of large surface ships. Compressor is one of the three main components of marine gas turbines. Its design technology has always been one of the key technologies in gas turbine design. Its performance has a direct impact on the overall performance of the gas turbine. The aerodynamic design technology of the compressor is the compressor design technology. One of the difficulties directly determines the overall performance, work stability and overall technical level of the compressor. [0003] In the early 20th century, the aerodynamic design of the compressor was based on a simple one-dimensional flow, and its efficiency and pressure ratio were relatively low. In the early 1950s, after Mr. Wu Zhonghua proposed t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/20G06F119/20
CPCG06F30/15G06F30/17G06F30/20G06F2119/20Y02T90/00
Inventor 任兰学王琦李冬万新超于景磊刘震金鹏洪青松初曙光刘云宁刘冰冰
Owner 中国船舶重工集团公司第七0三研究所
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