Tool and method for eliminating connection gaps of high-pressure turbine rotor blades

A technology for rotor blades and high-pressure turbines, applied in the direction of leakage prevention, engine components, machines/engines, etc., can solve problems such as reducing turbine efficiency, achieve the effects of eliminating connection gaps, low manufacturing and maintenance costs, and simple tool structure

Active Publication Date: 2017-12-29
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide a tool and method for eliminating the connection gap between the high-pressure turbine rotor blades in order to overcome the defects in the prior art that the gap between the high-pressure turbine rotor blades will reduce the efficiency of the turbine.

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  • Tool and method for eliminating connection gaps of high-pressure turbine rotor blades
  • Tool and method for eliminating connection gaps of high-pressure turbine rotor blades
  • Tool and method for eliminating connection gaps of high-pressure turbine rotor blades

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Embodiment Construction

[0028] In order to make the above objects, features and advantages of the present invention more comprehensible, specific implementations of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0029] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same numbers will be used throughout the drawings to refer to the same or like parts. In addition, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the description of the present invention may be selected by the applicant according to his or her judgment, and the detailed meanings thereof are set forth herein described in the relevant section of the description. Furtherm...

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Abstract

The invention provides a tool and method for eliminating connection gaps of high-pressure turbine rotor blades. The tool comprises an adjusting screw rod, an upper driving block, a squeezing block and a lower driving block. The squeezing block and the lower driving block are sequentially arranged on the adjusting screw rod in a penetration mode. When the adjusting screw rod is screwed, the upper driving block drives the adjusting screw rod to rotate to squeeze the squeezing block downward. The lower driving block drives the adjusting screw rod to rotate to squeeze the squeezing block upwards, so that the squeezing block protrudes outwards. In the method, the tool for eliminating the connection gaps of the high-pressure turbine rotor blades is adopted. By means of the tool and method for eliminating the connection gaps of the high-pressure turbine rotor blades, the connection gaps between the high-pressure turbine rotor blades and a turbine disk can be effectively eliminated, so that the diameter of high-pressure turbine blade tips is accurately obtained. The tool is simple in principle, simple in structure and low in manufacturing cost and maintenance cost.

Description

technical field [0001] The invention relates to the field of assembly and manufacture of aero-engines, in particular to a tool and method for eliminating connection gaps of high-pressure turbine rotor blades. Background technique [0002] The high-pressure turbine rotor unit is the main working part of an aero-engine, and generally consists of a drum, a sealing disc, a turbine disc, rotor blades, a tailgate, and a rear axle. The gap between the rotor and stator of the turbine (blade tip clearance) directly affects the performance characteristics of the turbine, thereby affecting the overall performance of the engine. [0003] In the prior art, excessive blade tip clearance will reduce the efficiency of the turbine, thereby leading to an increase in fuel consumption per unit thrust and an increase in gas temperature. Too small tip clearance will cause the turbine blades to scrape against the inner wall of the casing, causing vibration. In order to control the gap between th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D11/16
CPCF01D11/16
Inventor 胡一廷李琳朱希阁苏巧灵梁霄
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
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