Main speed reducer of fan of novel GTF aircraft engine

A technology of aero-engine and main reducer, which is applied in the field of gear transmission to achieve the effect of strong bearing capacity, lightening the mass and volume of the whole machine, and reducing the volume

Inactive Publication Date: 2014-10-01
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The multi-star wheel herringbone star transmission technology is adopted to solve the technical problem of small volume transmission of fan reducer and high power

Method used

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  • Main speed reducer of fan of novel GTF aircraft engine
  • Main speed reducer of fan of novel GTF aircraft engine
  • Main speed reducer of fan of novel GTF aircraft engine

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Embodiment Construction

[0030] The embodiment of the present invention is described with reference to the accompanying drawings. This implementation takes the new GTF aero-engine fan main reducer with 5 star wheels as an example, but is not limited to 5 star wheels. exist figure 1 Among them, the left end of the input shaft (3) is connected with the low-pressure turbine, and the low-pressure turbine transmits the rotational power to the input shaft (3). The input shaft (3) is installed on the left case cover (5) through a sliding bearing, and the input end cover (4 ) through the input shaft (3), position and seal it, the input end cover (4) is fixed on the outer surface of the left case cover (5) by bolts, and the left case cover (5) is fixed on the case body (6) by bolts ), the right end of the box body (6) and the right box cover (10) are fixed by bolts, the output end cover (14) plays a role in positioning the spherical roller bearing (11), and the output end cover (14) is fixed on the right side ...

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Abstract

The invention discloses a main speed reducer of a fan of a novel GTF aircraft engine. The main speed reducer of the fan of the novel GTF aircraft engine is characterized in that sun gears and star gears use integrated double helical teeth, an inner tooth ring A and an inner tooth ring B are helical internal gears connected with a gear coupling through helical external splines, the gear coupling is connected with an output shaft through a straight-tooth internal spline, the speed reducer does not have an independent planetary rack, all the star gears are fixed on a left box body cover through star gear shafts, each star gear only revolves on its axis, the space position of each star gear is not changed in running, a bush of each star gear shaft uses a special structure that the diameter of the central hole is gradually changed to automatically compensate the flexible deformation of a cantilever end, and each of the input shaft and star gear shafts comprises a cantilever and a hollow structure to increase the elastic deformation ability and play a role of storing lubricating oil. The main speed reducer of the fan of the novel GTF aircraft engine has beneficial effects of simple structure, simple technique, good uniform loading and floating effect, small speed reducer volume, strong bearing capacity, large transmission power and small vibration noise and is capable of realizing the fixed-point spray lubrication for the star gears and bearing.

Description

technical field [0001] The invention relates to the technical field of gear transmission, in particular to a novel GTF aero-engine fan final reducer. Background technique [0002] Geared Turbofan Engine (GTF), also known as GTF engine. Because it has many advantages such as low emission, low noise, low fuel consumption and low maintenance cost, it has been recognized by the market and has become one of the main development directions of the next generation of civil aeroengines. Reducing fuel consumption and reducing pollution emissions are the main development direction and "selling point" of the next generation of civil aviation engines. The main methods to reduce fuel consumption include: improving the thermal efficiency of the whole machine (increasing the outlet pressure of the compressor, increasing the temperature before the turbine), and improving the propulsion efficiency of the engine (reducing the exhaust speed and increasing the air flow). Increasing the efficie...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16H1/28F16H57/021
CPCF16H1/2836F16H57/021F16H57/023F16H57/043F16H2057/02039F16H2057/02091F16H2057/02095
Inventor 莫帅张以都吴琼
Owner BEIHANG UNIV
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