Ladder-shaped gap structure for gas compressor of aircraft engine

A technology of aero-engine and clearance structure, which is applied in the direction of machine/engine, liquid fuel engine, mechanical equipment, etc., can solve the problems of stability margin loss compressor efficiency, etc., to improve the stable working margin, facilitate processing, and simple layout. Effect

Active Publication Date: 2015-07-15
XECA TURBO TECH (BEIJING) CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But the disadvantage of this type of treatment casing is that the improvement of the stability margin comes at the expense of the efficiency of the compressor

Method used

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  • Ladder-shaped gap structure for gas compressor of aircraft engine
  • Ladder-shaped gap structure for gas compressor of aircraft engine

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Experimental program
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Embodiment 1

[0018] Embodiment 1: as figure 2 As shown, the aero-engine compressor described in this embodiment includes a rotor blade 1 and a casing shell 2, and the inner side wall of the casing casing 2 is provided with a stepped groove 3 with a small depth.

[0019] In order to improve the performance of the compressor and realize the organization and regulation of the complex flow in the tip area of ​​the compressor rotor blade, a stepped groove 3 with a depth equal to the blade tip gap is set on the compressor case shell 2, aiming at the design of the compressor Pursue different goals to determine the size of the blade tip clearance and the slotting position of the stepped groove, and design different stepped clearance structures on the rotor blade tip. If higher pressure ratio and efficiency are pursued in the design, the rotor blade tip clearance t1 shall be set as 0.3% of the axial chord length of the rotor blade tip, and the depth shall be introduced within the range of 60% to 1...

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Abstract

The invention provides a ladder-shaped gap structure for a gas compressor of an aircraft engine, and relates to the stability expanding technology of a high-load fan or a machine pressure gas machine of the aircraft engine. The gas machine of the aircraft engine comprises a blade and a cartridge receiver housing, wherein the position which corresponds to the inner side wall of the cartridge receiver housing is provided with a ladder-shaped peripheral groove with a certain depth and width in a machining way, the different ladder-shaped gap structure distributions can be obtained by optimizing the size of a matching gas and the position of the ladder-shaped peripheral groove, and the size and the position of a blockage group at the top region of the gas compressor can be effectively controlled due to the interaction of complex flow between the ladder-shaped groove and the top region of the gas compressor, so that the flowing area of the channel main flow can be improved, the stability work margin of the gas compressor can be improved, and the performance of the gas compressor can be improved.

Description

technical field [0001] The invention relates to a ladder-shaped gap structure for the fan and compressor of an aeroengine, which can realize the expansion, stability and efficiency of the fan and the compressor, and is especially suitable for high-performance aerogas turbine engines. Background technique [0002] The blade tip clearance in the turbomachinery is introduced to avoid friction between the rotating blade and the casing, and its size is about 0.3% to 1% of the axial chord length of the compressor rotor blade tip. Under the action of the pressure difference on both sides of the blade tip clearance, part of the fluid passes through the blade tip clearance to form a leakage flow. At the same time, due to the influence of the main flow, the leakage flow usually exists in the compressor rotor blade tip area in the form of blade tip leakage vortex. For fan / axial flow compressors, the negative impact of tip leakage flow is mainly reflected in leakage loss and clogging. T...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/40F04D29/66
Inventor 张学锋
Owner XECA TURBO TECH (BEIJING) CO LTD
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