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Shroud for splitter and rotor airfoils of a fan for a gas turbine engine

A technology for gas turbines and airfoils, applied in engine components, gas turbine devices, components of pumping devices for elastic fluids, etc., and can solve problems such as heavy, complex multi-stage fans, etc.

Active Publication Date: 2021-06-18
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Multi-stage fans in turbofan engines can be relatively complex, heavy, and require additional moving parts in the fan module

Method used

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  • Shroud for splitter and rotor airfoils of a fan for a gas turbine engine
  • Shroud for splitter and rotor airfoils of a fan for a gas turbine engine
  • Shroud for splitter and rotor airfoils of a fan for a gas turbine engine

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Embodiment Construction

[0072] Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. The same or similar symbols are used in the drawings and descriptions to refer to the same or similar parts of the present invention.

[0073] The following description is provided to enable those skilled in the art to make and use the described embodiments contemplated to practice the invention. However, various modifications, equivalents, variations and alternatives will still be apparent to those skilled in the art. Any and all such modifications, variations, equivalents and alternatives are intended to fall within the spirit and scope of the invention.

[0074] For the purposes of the following description, the terms "upper", "lower", "right", "left", "vertical", "horizontal", "top", "bottom", "landscape", "lengt...

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PUM

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Abstract

The invention relates to a shroud for a splitter and rotor airfoils of a fan for a gas turbine engine. Particularly, a fan for a gas turbine engine is provided. The fan includes a rotor including at least one rotor stage having a rotatable disk defining a flowpath surface and an array of rotor airfoils extending outward from the flowpath surface; an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement; and a shroud extending between the rotor airfoils and the splitter airfoils.

Description

technical field [0001] The present subject matter relates generally to gas turbine engines, or more specifically, to gas turbine engines having fan assemblies and shrouds for splitter airfoils and rotor airfoils. Background technique [0002] A gas turbine engine typically includes a fan and a core arranged in flow communication with each other. Additionally, the core of a gas turbine engine typically includes a compressor section, a combustion section, a turbine section, and an exhaust section in series flow order. In operation, air is provided from a fan to the inlet of the compressor section, where one or more axial compressors gradually compress the air until it reaches the combustion section. Fuel is mixed with compressed air and combusted in the combustion section to provide combustion gases. Combustion gases are channeled from the combustion section to the turbine section. The flow of combustion gases through the turbine section drives the turbine section and is th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/32F04D29/38F04D29/54F02K3/06
CPCF04D29/325F04D29/388F04D29/542F04D29/544F02K3/06F04D29/324F01D5/10F01D5/16F01D5/225F01D5/142F05D2260/96F01D5/146F01D5/34F01D5/141F01D9/041F05D2240/12F05D2220/36F05D2240/307F05D2240/35F02C7/36
Inventor A·L·小迪皮特罗T·J·亚历山大J·卡波齐A·R·瓦迪亚A·布雷斯-斯特林费罗
Owner GENERAL ELECTRIC CO