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Aerodynamic design method of high-performance ship gas turbine compressor

A pneumatic design and compressor technology, applied in geometric CAD and other directions, can solve problems such as small adaptability and complicated operation

Inactive Publication Date: 2020-03-27
中国船舶重工集团公司第七0三研究所
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0006] The purpose of the present invention is to solve the problem of complex aerodynamic design operation and small adaptable range of the existing technology based on the ship power of our country's ship gas turbine compressor, and now proposes a high-performance ship gas turbine compressor aerodynamic design method

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  • Aerodynamic design method of high-performance ship gas turbine compressor
  • Aerodynamic design method of high-performance ship gas turbine compressor
  • Aerodynamic design method of high-performance ship gas turbine compressor

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specific Embodiment approach 1

[0021] Specific implementation mode one: refer to figure 1 To illustrate this embodiment, the aerodynamic design method of a high-performance marine gas turbine compressor described in this embodiment includes the following steps:

[0022] Step 1. Refer to figure 1 , according to the design requirements and goals, and in accordance with the overall design requirements of the compressor, the one-dimensional inverse problem design of the multi-stage axial flow compressor is carried out, and multiple schemes are obtained. At the same time, the designed schemes can also be stored as data resources in the compressor pneumatic in the design database;

[0023] The basic parameters of the compressor are selected according to the average radius aerodynamic design specification. Many parameters in this process are selected based on design experience. You can check the relevant unit design data with the help of the compressor basic parameter database, and perform multi-plan optimization...

specific Embodiment approach 2

[0026] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that the step 1 is designed to violate the problem, and the main tasks include: according to the given flow rate and pressure ratio, estimate the efficiency of the compressor and the main geometric parameters, based on experience relationship, determine the preliminary design scheme of the compressor, and obtain the basic conditions of the compressor's rotation angle, blade height, chord length, number of blades, inner and outer diameters, and angle of attack (the main parameters of the one-dimensional design of the compressor are shown in Table 1):

[0027] Table 1 Main parameters of one-dimensional aerodynamic design of a typical compressor

[0028]

[0029] In the process of designing one-dimensional inverse problems, attention should be paid to the selection of the following parameters:

[0030] Axial speed: The selection of the axial speed of the inlet stage needs to compr...

specific Embodiment approach 3

[0032]Embodiment 3: The difference between this embodiment and Embodiment 1 or 2 is that the step 1 is to calculate and optimize the characteristics of the compressor; the specific process is:

[0033] In the one-dimensional characteristic calculation and optimization stage, the AXIAL software module in the Concepts-NREC engineering design system is used. This software provides the design calculation of multi-stage axial flow compressors and turbomachinery, as well as the existing units or design schemes. The analysis function can also be used to predict and analyze the performance of turbomachinery under variable conditions. In the one-dimensional characteristic calculation and optimization stage, the analysis mode is adopted, and the design results of the compressor flow obtained by the one-dimensional inverse problem, that is, the geometric parameters of the blade rows at all levels, are checked and calculated by means of the analysis mode of the program software, and repeat...

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Abstract

The invention discloses an aerodynamic design method of a high-performance ship gas turbine compressor, aiming to solve the problems of complex pneumatic design operation and small application range of a ship gas turbine compressor based on ship power in China in the prior art. The aerodynamic design method of the high-performance ship gas turbine compressor comprises the steps: according to design requirements and targets and the overall design requirements of the compressor, conducting one-dimensional inverse problem design of a multi-stage axial flow compressor, and on the basis of a one-dimensional design scheme, performing S2 through-flow inverse problem design; comparing and analyzing three-dimensional matching characteristics of the gas compressor by adopting a multi-stage gas compressor three-dimensional numerical simulation method, carrying out three-dimensional numerical simulation, and comparing and analyzing the three-dimensional numerical simulation with one-dimensional and S2 calculation results; and returning the obtained data to the S2 through-flow inverse problem design, and repeatedly iterating to complete the S2 through-flow inverse problem design and the blade modeling design. The aerodynamic design method can be applied to all fields of gas turbines, including military, energy, electric power, traffic, environmental protection and the like.

Description

technical field [0001] The invention relates to an aerodynamic design method of a high-performance marine gas turbine compressor. Background technique [0002] The high-power gas turbine for ships is the key and core equipment for the development of large surface ships in my country. Long-term follow-up and imitation have caused the lack of complete independent design capabilities in the development of ship gas turbine compressors in my country, resulting in problems such as imperfect design methods and systems, low design stability, and lack of specialized design criteria. It is urgent to develop ship gas turbines. Fundamental research on compressor aerodynamics. [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 two types of flow surface theories (S1 and S2 flow surfaces), the flow-through progr...

Claims

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Application Information

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IPC IPC(8): G06F30/17
Inventor 任兰学姜斌王琦
Owner 中国船舶重工集团公司第七0三研究所
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