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Gas turbine engine

A gas turbine and engine technology, applied in the direction of engine manufacturing, engine components, machines/engines, etc., can solve the problems of increasing the amount of fuel incineration, increasing resistance, etc.

Active Publication Date: 2017-06-20
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Furthermore, the inventors of the present disclosure discovered that longer nacelle assemblies can create an increased amount of drag, especially with relatively large fans, which can thus increase the amount of fuel burned

Method used

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  • Gas turbine engine
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Embodiment Construction

[0092] 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. Like or similar reference numerals are used in the drawings and description to indicate like or similar parts of the present invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one element from another, and are not intended to denote the position or importance of individual elements. . The terms "upstream" and "downstream" refer to relative directions with respect to fluid flow in a fluid channel. For example, "upstream" refers to the direction of fluid flow from, and "downstream" refers to the direction of fluid flow to.

[0093] Referring now to the drawings, wherein like numerals indicate like elements throughout, figure 1 is a schematic cross-sectional ...

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Abstract

A gas turbine engine includes a fan and a core in flow communication with the fan. The core includes an aftmost turbine, and the aftmost turbine includes an aftmost stage of rotor blades. The gas turbine engine also includes a nacelle assembly having a translating and rotating thrust reverser system and enclosing the fan and at least a portion of the core. The nacelle assembly defines a nacelle assembly length between a forward lip and an aft edge. Additionally, the gas turbine engine defines an engine length between the forward lip of the nacelle assembly and the aftmost stage of rotor blades of the aftmost turbine. A ratio of the engine length to the nacelle assembly length is greater than about 0.5 and less than about 1.

Description

technical field [0001] The subject matter generally relates to a gas turbine engine. Background technique [0002] A turbofan engine generally includes a fan and a core arranged in flow communication with each other. The core of a turbofan engine generally includes, in series flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air provided to the core flows through the compressor section, where one or more axial compressors progressively compress the air until it reaches the combustion section. Fuel is mixed with compressed air and burned in the combustion section to provide combustion gases. Combustion gases are sent from the combustion section to the turbine section. The flow of combustion gases through the turbine section drives the turbine section and is then sent through the exhaust section, eg, to the atmosphere. [0003] A fan generally includes a plurality of rotatable fan blades that generate a flow of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/06F02K3/02
CPCF02K3/02F02K3/06F01D25/16F02K1/06F02K1/72F02C7/04F05D2250/42F05D2250/10F01D5/02F01D5/12F01D15/12F01D25/24F02K1/70F05D2220/36
Inventor B·W·米勒M·T·弗拉纳A·R·斯图尔特
Owner GENERAL ELECTRIC CO