Turbomachine assembly comprising fan blades with an extended trailing edge

A component and fan technology, applied in the field of bypass gas turbine engines, can solve the problems of deteriorating operation and low efficiency of superchargers

Active Publication Date: 2021-09-21
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

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Method used

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  • Turbomachine assembly comprising fan blades with an extended trailing edge
  • Turbomachine assembly comprising fan blades with an extended trailing edge
  • Turbomachine assembly comprising fan blades with an extended trailing edge

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Embodiment Construction

[0033] In the present application, upstream and downstream are defined relative to the normal flow direction of gas in the gas turbine engine 1 . In addition, the axis of rotation of the gas turbine engine is referred to as the radial axis of symmetry X of the gas turbine engine. The axial direction corresponds to the direction of the axis X of the gas turbine engine, and the radial direction is a direction perpendicular to and passing through this axis. Similarly, an axial plane is a plane containing the axis X of the gas turbine engine, and a radial plane is a plane perpendicular to and passing through this axis X. A tangential (or circumferential) direction is a direction perpendicular to this axis X and not passing through it. Unless otherwise stated, inner (or inner) and outer (or outer) are used with reference to a radial direction, respectively, such that an inner portion or face of an element (i.e., radially inner) is smaller than an outer portion or face of the same ...

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PUM

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Abstract

The invention relates to a turbomachine assembly (1) comprising a fan (2) and a booster drum-type part (3), the fan (2) comprising: blades (20) comprising an airfoil (23) and an extension (30) mounted on and attached to the trailing edge (25) of the airfoil (23), a fan (2) disc (10) and a series of inter-blade platforms (16), the extension (30) of each blade (20) extending beyond the downstream face (14) of the fan (2) disc (10) in the direction of the upstream edge (4) of the part (3) and covering, at least partially, the cavity (6) between the fan (2) and the part (3).

Description

technical field [0001] The present invention relates generally to the field of bypass gas turbine engines, and more particularly to the fans of these gas turbine engines and their interaction with the inlet of the main duct. Background technique [0002] A bypass gas turbine engine generally includes a fan, a primary annular flow duct, and a secondary annular flow duct from upstream to downstream in the direction of air flow. Therefore, the mass of air sucked by the fan is divided into a main flow circulating in the main flow duct and a secondary flow concentric with the main flow and circulating in the secondary flow duct. [0003] The main flow conduit passes through the body, which includes one or more stages of compressors (such as low-pressure compressors and high-pressure compressors), a combustor, one or more stages of turbines (such as high-pressure turbines and low-pressure turbines), and gas discharge nozzles . [0004] The fan includes a rotor disk carrying a pl...

Claims

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Application Information

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IPC IPC(8): F01D5/14F01D5/30F01D11/00
CPCF01D5/145F01D5/3007F01D11/008F05D2240/304F05D2220/36F05D2240/55F05D2300/10F05D2300/603
Inventor 保罗·安托万·弗雷斯托薇薇安·米卡尔·考提尔斯蒂芬·罗杰·马希亚斯威廉·亨利·约瑟夫·里埃拉
Owner SAFRAN AIRCRAFT ENGINES SAS
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