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A kind of compressor, gas turbine and compressor expansion stability and efficiency method

A technology for compressors and hubs, applied in the direction of machines/engines, mechanical equipment, liquid fuel engines, etc., to achieve good sealing performance, inhibit the development of separated vortexes, and reduce losses

Active Publication Date: 2019-08-02
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the negative impact on the efficiency of the circumferential groove and axial seam casing has always been the bottleneck that restricts the further improvement of its expansion and stability capabilities.

Method used

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  • A kind of compressor, gas turbine and compressor expansion stability and efficiency method
  • A kind of compressor, gas turbine and compressor expansion stability and efficiency method
  • A kind of compressor, gas turbine and compressor expansion stability and efficiency method

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Embodiment Construction

[0023] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

[0024] In order to improve the thrust-to-weight ratio and reduce fuel consumption, modern turbofan engines pursue high bypass ratio, high pressure ratio and high temperature before the turbine. The total pressure ratio of the entire compressor is one of the key performance indicators. For example, the pressure ratio of GE9x can reach 60 (including the root of the fan)! A certain type of commercial aeroengine CJx being developed in my country has a design total pressure ratio of 43. The supercharging of the gas turbine is completed by three parts. First, the root of the fan matches the connotation channel, followed by the low-pressure compressor (also known as Booster, often translated as supercharging stage), and finally ...

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Abstract

The invention provides a gas compressor, a gas turbine with the gas compressor and a gas compressor stability enhancement and efficiency improvement method. According to the gas compressor, through holes are formed in the wall surface, located on the high-pressure stage, of a casing, through holes are formed in the wall surfaces, located on the blade tops of low-pressure stage movable blades, of the casing, through holes are formed from the root portions of low-pressure stage stationary blades to suction surfaces of blade surfaces, and the through holes formed in the wall surface, located on the high-pressure stage, of the casing, the through holes formed in the wall surfaces, located on the blade tops of the low-pressure stage movable blades, of the casing and the through holes formed from the root portions of the low-pressure stage stationary blades to the suction surfaces of the blade surfaces are connected in sequence, so that a self-circulation mechanism with a suction-ejection function is formed. Part of gas sucked from the high-pressure stage of the gas compressor is guided back to the leading edges of the blade tops of the low-pressure stage movable blades and the suction surfaces of the blade surfaces of the low-pressure stage stationary blades through the self-circulation mechanism, and is ejected, and therefore the stall margin of the gas compressor is broadened, flow separation is restrained, and the efficiency of the gas compressor is effectively improved.

Description

technical field [0001] The invention relates to the field of energy and power, in particular to a compressor, a gas turbine using the compressor, and a method for expanding stability and efficiency of the compressor. Background technique [0002] An axial flow compressor includes moving blades, vanes, hubs and casings. The moving blades, stationary blades and hubs are all placed in the casing. The blade edge is fixed on the hub and can rotate together with the hub. The vane edge is fixed on the casing and remains stationary all the time. And the moving blades and stationary blades are arranged alternately and at intervals in the axial direction (that is, the axial direction of the hub). In the circumferential direction (that is, the circumferential direction of the hub), a row of moving blade blades and a row of stationary blade blades followed constitute a stage of the compressor. A multi-stage axial compressor consists of multiple stages. As the compressor stage load ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/68F04D29/54
CPCF04D29/542F04D29/545F04D29/682F04D29/684
Inventor 李继超杜娟李艺雯林峰张宏武聂超群
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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