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Engine guide vane for aviation

A guide vane and engine technology, applied in the direction of engine components, machines/engines, blade support components, etc., can solve problems such as increased fuel consumption, achieve shortened life and good sealing effect

Inactive Publication Date: 2018-01-16
成都鑫晨航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to solve the problem of increased fuel consumption caused by the blade tip clearance existing in the guide vanes of aviation engines. The present invention provides a guide vane of aviation engines.

Method used

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  • Engine guide vane for aviation
  • Engine guide vane for aviation
  • Engine guide vane for aviation

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] The technical scheme of the present embodiment is:

[0030] An aircraft engine guide vane, comprising a blade main body 1, the blade main body 1 is connected with a sealing mechanism 2; the sealing mechanism 2 includes a hard rubber layer 201, a spring layer 202, a fiber cloth layer 203 and a brush connected sequentially from bottom to top Layer 204; the hard rubber block 201 is connected to the blade tip of the blade main body 1;

[0031] The hard rubber layer 201 is provided with a first flow guide groove 2012 and a second flow guide groove 2015 parallel to each other, and a first flow guide groove 2012 and a second flow guide groove 2015 are provided between the first flow guide groove 2012 and the second flow guide groove 2015. 2012 and the third diversion groove 2013 connected to the second diversion groove 2015;

[0032] A fourth diversion groove 2014 communicating with the third diversion groove 2013 is also provided between the first diversion groove 2012 and t...

Embodiment 2

[0036] On the basis of Embodiment 1, the technical solution of this embodiment is: the fiber cloth layer 203 includes a cotton and linen fiber cloth 2032 fixedly connected to the hard rubber layer 201, and the outer surface of the cotton and linen fiber cloth 2032 is covered with The soft rubber 2031 has a number of guide holes 2033 on the soft rubber 2031 .

[0037] Such as image 3 and Figure 4 As shown, the liquid fuel flows into the cotton and linen fiber cloth 2032 from a part of the guide hole 2033, and due to the surface tension of the liquid fuel, it forms a thin film in the gap in the cotton and linen fiber cloth 2032 to play a sealing effect; The liquid fuel flows out from the other guide hole 2033 to reduce the weight of the sealing mechanism 2, thereby reducing the energy consumption of the engine itself.

Embodiment 3

[0039] On the basis of Embodiment 1, the technical solution of this embodiment is: the brush layer 204 includes several steel wire brushes 2041 fixedly connected to the fiber cloth layer 203, and each of the steel wire brushes 2041 is formed by intertwining several steel wire strips .

[0040] Such as image 3 and Figure 5 As shown, the wire brush 2041 has a certain degree of softness and can fit well with the casing wall so that the sealing effect is optimal and can well adapt to changes in the casing cavity; the wire brush 2041 is formed by intertwining several steel wire strips This makes the wire brush 2041 easy to replace when it cannot be used due to wear and tear.

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Abstract

The invention discloses an engine guide vane for aviation, and belongs to the technical field of engines for the aviation. The engine guide vane comprises a vane main body, and a sealing mechanism isconnected to the vane main body; the sealing mechanism comprises a hard rubber layer, a spring layer, a fiber cloth layer and a brush layer which are connected in sequence from bottom to top; the hardrubber block is connected with a vane tip of the vane main body; the hard rubber layer is the hard rubber block, and a first diversion trench, a second diversion trench, a third diversion trench anda fourth diversion trench which are parallel to one another are formed in the outer surface of the hard rubber block; the first diversion trench, the second diversion trench and the fourth diversion trench all extend to the edge of the hard rubber layer to form six diversion openings. Accordingly, liquid fuel in the hard rubber block or fuel steam obtained after gasification can be led out, the phenomenon that the liquid fuel or the fuel steam obtained after gasification is stacked in hard rubber, and then the hard rubber is corroded is avoided, an then the service life of the sealing mechanism is shortened.

Description

technical field [0001] The invention belongs to the technical field of aviation engines, and in particular relates to an aviation engine guide vane. Background technique [0002] Because there is a certain gap between the engine turbine rotor blades and the stator casing, the gas will leak under the action of the pressure difference between the front and rear pressure surfaces and suction surfaces of the blades, which will affect the engine efficiency. British Rolls-Royce (RR) research on modern gas turbine engines shows that for every 1% increase in blade tip clearance, the efficiency will decrease by about 1.5%, and the fuel consumption rate will increase by about 2%. The fuel consumption rate not only affects the performance of the engine, but also affects its life-cycle cost. According to the analysis of the CF5-50 engine by General Electric (GE), the impact of the blade tip clearance on the fuel consumption rate accounts for about 10% of the total loss of the blade shap...

Claims

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Application Information

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IPC IPC(8): F01D5/14F01D11/12
Inventor 石存岭
Owner 成都鑫晨航空科技有限公司
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