Ship gas turbine compressor performance optimization method based on three-dimensional flow field analysis
A technology of three-dimensional flow field and optimization method, applied in design optimization/simulation, instrument, geometric CAD, etc., can solve problems such as low efficiency and pressure ratio, and achieve the effect of eliminating airflow separation, improving adiabatic efficiency, and reducing time consumption
Active Publication Date: 2021-09-24
中国船舶重工集团公司第七0三研究所
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[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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[0023] The present invention is described in more detail below in conjunction with accompanying drawing example:
[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 cross-section for optimal calculation; usually, different relative height positions along the blade height are used as the characteristic cross-section, and generally 5 or 7 cross-sections are selected, and the distance between the cross-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 speed of the rotor blade inlet W 1 , the relative speed of the rotor blade outlet...
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The invention aims to provide a ship gas turbine compressor performance optimization method based on three-dimensional flow field analysis, and the method comprises the steps: taking a design working condition point as a reference, checking the flow field velocity distribution or Mach number distribution of different section heights from a first column of blades to a last column of blades, determining the flow matching condition of the flow field, and determining the flow matching condition of the flow field; pertinently judging the attack angle ranges of different section heights of each blade row, determining the blade inlet airflow angle and outlet airflow angle deviation, finely adjusting the blade inlet geometric angle and the blade outlet geometric angle, and completing optimization adjustment; for the separation of the end area, properly adopting the end bending technology in the modeling process of the stator blade, and optimizing the design. According to the method, the specific part where separation flow is generated can be predicted, the blade shape is adjusted to eliminate separation or reduce a separation area, and therefore the effects of improving efficiency and increasing the stall margin of the gas compressor are achieved.
Description
technical field [0001] The invention relates to a gas turbine performance optimization method, in particular to a compressor performance optimization method. Background technique [0002] High-power gas turbines for ships are the key and core equipment of large surface ships. The compressor is one of the three main components of the ship gas turbine. Its design technology has always been one of the key technologies in the design of the gas turbine. 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 most difficult points directly determines the overall performance, working stability characteristics 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, aft...
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Login to View More 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