Inclusive clamp assembly for aeroengine and aeroengine
An aero-engine, inclusive technology, applied in the direction of engine components, engine lubrication, machine/engine, etc., can solve the problems of free turbine being restricted in a safe area, free turbine falling off, etc., to reduce the probability of obstruction, prevent overturning and falling out, The effect of reducing the occupied space
Active Publication Date: 2018-11-09
CHINA HANGFA SOUTH IND CO LTD
View PDF5 Cites 0 Cited by
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
[0006] The present invention provides an inclusive clip assembly for aero-engines and an aero-engine to solve the technical problem that the existing aero-engine inner-included cover device cannot restrict the free turbine to a safe area, and there is still a risk of the free turbine falling off and flying out
Method used
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View moreImage
Smart Image Click on the blue labels to locate them in the text.
Smart ImageViewing Examples
Examples
Experimental program
Comparison scheme
Effect test
Embodiment Construction
[0027] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.
[0028] figure 1 It is a schematic split structure diagram of an inclusive clamp assembly for an aero-engine according to a preferred embodiment of the present invention; figure 2 It is a structural schematic diagram of the assembling part of the inclusive clamp assembly in the preferred embodiment of the present invention; image 3 It is a schematic diagram of the assembled structure in the aero-engine of the preferred embodiment of the present invention; Figure 4 It is a schematic diagram of the assembled structure of the aero-engine of the preferred embodiment of the present invention.
[0029] Such as figure 1As shown, the inclusive clip assembly for the aero-engine of this embodiment includes a clamp assembly for fixing on the reducer mounting section a...
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More PUM
Login to View More Abstract
The invention discloses an inclusive clamp hoop assembly used for an aircraft engine and the aircraft engine. The inclusive clamp hoop assembly used for the aircraft engine comprises a first inclusive clamp hoop and a second inclusive clamp hoop, and the inclusive clamp hoops are used for being fixed to reduction gear mounts, surrounding the outside of a free turbine bearing base, and limiting the radial movement range of the free turbine bearing base in an elastic buffer mode so as to prevent the free turbine bearing base from flying off during disassembly. The first inclusive clamp hoop and the second inclusive clamp hoop are arranged coaxially and tightly attached to form the assembly so as to together surround the outside of the free turbine bearing base to increase the area that the inclusive clamp hoops make contact with the disassembled free turbine bearing base, so that the situation that the stress on the outer surface of the free turbine berating base is concentrated and accordingly the free turbine berating base is deformed and fractured is prevented, and the situation that the free turbine berating base is overturned laterally and slipped off is prevented. The inclusive clamp hoop forms multi-stage impact force buffer and limiting with the free turbine berating base, the stress concentration generated during the disassembly of the free turbine berating base is reduced, and splashing destruction generated by fractures and crushing of the free turbine bearing base is prevented.
Description
technical field [0001] The invention relates to the technical field of aero-engine structures, in particular to an inclusive clip assembly for an aero-engine. Furthermore, the present invention also relates to an aero-engine comprising the above-mentioned containment clip assembly for an aero-engine. Background technique [0002] The body part of the turboshaft engine consists of six parts: accessory drive, compressor, gas generator, free turbine, reducer and exhaust section. The role of the accessory transmission unit is to transmit power and drive the accessories, and provide rigid support for the engine. The front end is connected to the helicopter through the front bracket to form the front fulcrum of the engine installation; the rear end is connected to the reducer unit through the power shaft to form the rear fulcrum of the engine installation. . The free turbine unit is installed between the gas generator and the reducer to convert gas kinetic energy into mechanical...
Claims
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More Application Information
Patent Timeline
Login to View More Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/20F02C7/06F01D25/16
CPCF01D25/164
Inventor 胡承邦范丽萍刘飞亭
Owner CHINA HANGFA SOUTH IND CO LTD