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A Design Method of Rotation Angle Law of Transducer Vane in Axial Flow Compressor of Marine Gas Turbine under Low Operating Conditions

A technology for axial flow compressors and gas turbines, which is applied in computer-aided design, mechanical equipment, machines/engines, etc., and can solve the difficulty in designing the law of rotation angles of joint control of multiple rows of transducible guide vanes in compressors, and the surge in the number of samples of angle combination schemes, etc. problems, to simplify the workload of designers, improve surge margin indicators, and reduce resource and time consumption

Active Publication Date: 2022-04-08
NO 703 RES INST OF CHINA SHIPBUILDING IND CORP
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  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

At the same time, with the gradual increase in the number of transducible lobe rows and the increasingly flexible control methods of transducible lobe, the number of angle combination schemes between multi-row transducible lobes has increased sharply, which gives the compressor multi-row transducible lobe The design of joint regulation and rotation angle law brings more difficulties and challenges

Method used

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  • A Design Method of Rotation Angle Law of Transducer Vane in Axial Flow Compressor of Marine Gas Turbine under Low Operating Conditions
  • A Design Method of Rotation Angle Law of Transducer Vane in Axial Flow Compressor of Marine Gas Turbine under Low Operating Conditions
  • A Design Method of Rotation Angle Law of Transducer Vane in Axial Flow Compressor of Marine Gas Turbine under Low Operating Conditions

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Embodiment Construction

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

[0033] combine Figure 1-2 , a specific embodiment of the method for designing the rotation angle law of a ship's gas turbine axial flow compressor under low working conditions can be realized by the following steps:

[0034] (1) Select the characteristic section for the calculation of the transducer vane angle;

[0035] (2) Extract the main aerodynamic parameters of the compressor at the design point (the rotation angle of all the transmissible guide vanes is 0° at this time) at the characteristic cross-section position of each row of transducible guide vanes adjacent to the rear row blades, including: inlet axial velocity C 1a , peripheral speed U, inlet absolute airflow angle α 1 and inlet relative airflow angle β 1 ;

[0036] (3) Calculate the rotor blade circumferential speed U' at the reduced speed according to the converted rotational speed n' of the co...

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Abstract

The purpose of the present invention is to provide a method for designing the rotation angle law of steerable guide vanes under low working conditions of a marine gas turbine axial flow compressor, extracting the aerodynamic parameters at the characteristic cross-section positions of the adjacent rear discharge vanes of each row of steerable guide vanes of the compressor, and decompressing the compressor The reduced rotating speed under low working conditions and the reduced rotating speed at the design point are used to calculate the peripheral speed of the moving blades; a reduced flow value is set to calculate the axial speed of the inlet of each row of moving blades; given the expected inlet angle of attack of the moving blades of the next stage, each After the row of steerable guide vanes rotates, the relative airflow angle of the inlet of the next stage of the bucket is calculated, and the rotation angle of each row of steerable guide vanes is obtained, and the rotation angle law of the compressor steerable guide vane at different reduced rotational speeds is obtained. The invention can quickly obtain an ideal law of joint regulation and control of multiple rows of transductable guide vanes, effectively reduces resource and time consumption in the design process, simplifies the workload of designers, and can effectively improve the compressor under low working conditions. The surge margin index is very suitable for engineering design applications.

Description

technical field [0001] The invention relates to a design method of a gas turbine, in particular to a design method of a ship gas turbine compressor. 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. In order to adapt to the technical and tactical requirements during the ship's navigation, the ship's gas turbine must be able to operate efficiently with a margin under low working conditions while ensuring the performance of the design point. 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 turbi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/28F04D27/02G06F113/08
CPCG06F30/15G06F30/28F04D27/0246G06F30/17G06F2113/08
Inventor 林枫王琦万新超李冬王廷任兰学张舟洪青松
Owner NO 703 RES INST OF CHINA SHIPBUILDING IND CORP
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