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Supersonic turbofan engine

A turbofan engine, turbine engine technology, applied in the direction of engine functions, machines/engines, aircraft parts, etc., can solve problems such as restricting the use of gas turbine engines, noise limit restrictions, acoustic interference, etc.

Inactive Publication Date: 2018-06-22
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

however, these gas turbine engines may generate a relatively large amount of acoustic disturbance (ie, noise) when operating at supersonic flight speeds
While this is generally acceptable for military applications, this acoustic disturbance may limit the use of gas turbine engines in commercial applications given the noise limits of commercial aircraft on land

Method used

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  • Supersonic turbofan engine
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Embodiment Construction

[0037] 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 reference numerals are used in the drawings and description to refer to the same or similar parts of the present invention. As used herein, the terms "first," "second," and "third" are used interchangeably to distinguish one component from another, and are not intended to indicate the location or importance of individual components. The terms "upstream" and "downstream" refer to relative directions with respect to fluid flow in a fluid path. For example, "upstream" refers to the direction from which fluid flows, and "downstream" refers to the direction to which fluid flows.

[0038] Referring now to the drawings, wherein like numerals indicate like elements throughout, figure 1 is a schematic cro...

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PUM

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Abstract

A supersonic turbofan engine includes a fan section having a single-stage fan defining a fan pressure ratio greater than 1.9. the supersonic turbofan engine also includes a core turbine engine defining a core air flowpath. A nacelle at least partially surrounds the fan of the fan section and the core turbine engine. The supersonic turbofan engine defines a bypass ratio, the bypass ratio being greater than or equal to three.

Description

technical field [0001] The subject matter relates generally to a gas turbine engine, or, more specifically, to a gas turbine engine bearing assembly configuration. Background technique [0002] A gas turbine engine generally includes a fan and a core arranged in flow communication with each other. The core of a gas turbine engine generally includes a compressor section, a combustion section, a turbine section and an exhaust section in serial flow order. In at least some gas turbine engines, a nacelle is also included that extends around and encompasses at least a portion of the fan and core. The shroud may be supported by the core and / or fan and mechanically connected to the core and / or fan by a plurality of struts. For gas turbine engines including single stage fans, the struts are positioned in relatively close proximity to the fan blades so that they can act as the fan's outlet guide vanes. [0003] For gas turbine engines operating at supersonic flight speeds (ie, fli...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/075F02K3/06
CPCF02K3/06F02K3/075F05D2220/80F05D2220/323B64D29/00F05D2260/96
Inventor B.W.米勒M.J.拉里丘塔D.R.德怀尔J.D.克莱门茨K.谢菲尔T.O.莫尼斯
Owner GENERAL ELECTRIC CO