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Turbine engine frame incorporating splitters

A technology for turbine engines and separators, used in machine/engine, engine components, liquid fuel engines, etc., to solve problems such as undesired aerodynamic interactions between rotating airfoils and downstream frame structures

Active Publication Date: 2018-06-08
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] A problem with these designs is that they can cause undesired aerodynamic interactions between the rotating airfoil and the downstream airframe structure

Method used

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  • Turbine engine frame incorporating splitters
  • Turbine engine frame incorporating splitters
  • Turbine engine frame incorporating splitters

Examples

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Embodiment Construction

[0037]Referring to the drawings, wherein like reference numerals refer to like elements throughout the views, FIG. 1 shows an exemplary gas turbine engine 10 . Although the illustrated example is a high-bypass turbofan engine, the principles of the present invention are also applicable to other types of engines, such as low-bypass turbofan engines, turbojet engines, turboprop engines, and the like. Engine 10 has a longitudinal centerline or axis 11 and an outer stationary annular core casing 12 disposed concentrically about and coaxially along axis 11 .

[0038] It should be noted that the terms "axial" and "longitudinal" used in this specification both refer to directions parallel to the central axis 11, while "radial" refers to directions perpendicular to the axial direction, while "tangential" or "circumferential ” means the directions perpendicular to the axial and tangential directions. As used in this specification, the term "front" or "front" refers to a location relat...

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PUM

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Abstract

The invention provides a turbine engine frame apparatus. The frame apparatus includes a turbomachinery stage discharging into a downstream flow path, the stage including a rotor carrying an array of axial-flow rotor airfoils; and a frame disposed downstream of the turbomachinery stage, the frame including: a support structure comprising at least one of a hub and an annular casing; an annular arrayof stationary struts carried by the support structure, each strut having an airfoil shape with spaced-apart pressure and suction sides extending between a leading edge and a trailing edge thereof, the stationary struts defining spaces therebetween; and the stationary struts defining spaces therebetween; and a plurality of splitters carried by the support structure, the splitters positioned in thespaces between the stationary struts, wherein at least one of a chord dimension of the splitters and a span dimension of the splitters is less than the corresponding dimension of the stationary struts.

Description

technical field [0001] The present invention relates generally to gas turbine engines, and more particularly to stationary frames in such engines. Background technique [0002] A gas turbine engine includes a compressor, combustor, and turbine in series fluid communication. The turbine is mechanically connected to the compressor, and three parts define the core of the turbine. The core is operable to generate a flow of hot, pressurized combustion gases. The core forms the basis of several types of aircraft engines, such as turbojets, turboprops and turbofans. [0003] Designers and engineers are continually working to produce gas turbine engines with higher output and lower fuel consumption. In newer gas turbine engine designs, including extensions of existing designs with high power performance (ie, "growth designs"), the turbine exit Mach number can be increased. [0004] One problem with these designs is that they may cause undesirable aerodynamic interactions between...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/02
CPCF01D5/02F01D9/02F01D5/143F01D5/146F04D29/542Y02T50/60
Inventor J.D.克莱门茨G.塞沙里M.马诺哈兰R.阿文查A.R.瓦迪亚
Owner GENERAL ELECTRIC CO