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Turbine engine rack including separator

A technology for separators and turbines, applied in the direction of machines/engines, engine components, liquid fuel engines, etc., which can solve the problem of undesired aerodynamic interaction between rotating airfoils and downstream frame structures

Active Publication Date: 2022-02-15
GENERAL ELECTRIC CO
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  • Abstract
  • Description
  • Claims
  • Application Information

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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 rack including separator
  • Turbine engine rack including separator
  • Turbine engine rack including separator

Examples

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Embodiment Construction

[0037] Referring to the drawings, wherein like reference numerals denote like elements throughout the several views,figure 1 An exemplary gas turbine engine 10 is shown. 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 loca...

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Abstract

The present application provides a frame apparatus for a turbine engine comprising: a turbine stage discharging into a downstream flow path, the turbine stage including a rotor carrying an array of axial rotor airfoils; and A frame downstream of the turbine stage, the frame comprising: a support structure including at least one of a hub and an annular casing; an annular array of fixed struts carried by the support structure, each strut having an airfoil shape having spaced apart pressure and suction sides extending between a leading edge and a trailing edge thereof, the fixed struts defining a space therebetween; and the fixed struts defining a space between them; the space between them; and a plurality of separators carried by said support structure, said separators being located in said spaces between said fixed struts, wherein said separators have a chordal dimension and said separators At least one of the span dimensions is smaller than a corresponding dimension of the fixed strut.

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 Patents(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
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