Thrust reverser for high bypass turbofan engine

Matta, R K; Bhutiani, P K

Title: Thrust reverser for high bypass turbofan engine

Full Record
Other Related Research

Abstract

This patent describes a thrust reverser for a gas turbine engine of the type which includes an outer wall spaced from the center body of a core engine to define a bypass duct therebetween. The thrust reverser comprising: circumferentially displaced blocker doors, each of the doors being movable between a normal position generally aligned with the outer wall and a thrust reversing position extending transversely of the bypass duct for blocking the exhaust of air through the bypass duct and directing the air through an opening in the outer wall for thrust reversal; each of the blocker doors being of lightweight construction and including a pit in the inner surface thereof in the normal position; means for covering the pit during normal flow of air through the bypass duct to reduce the pressure drop in the bypass duct and to reduce noise. The covering means including a pit cover hingedly mounted at one end thereof on the blocker door and means of biasing the pit cover away from the blocker door to a position providing smooth flow of air through the bypass duct during normal operation.

Inventors:: Matta, R K; Bhutiani, P K

Publication Date:: Tue May 08 00:00:00 EDT 1990

OSTI Identifier:: 6715238

Patent Number(s):: US 4922712; A

Application Number:: PPN: US 7-173800A

Assignee:: General Electric Co., Cincinnati, OH

Resource Type:: Patent

Resource Relation:: Patent File Date: 28 Mar 1988

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS; GAS TURBINE ENGINES; THRUSTERS; BYPASSES; DESIGN; ENGINES; HEAT ENGINES; INTERNAL COMBUSTION ENGINES; 330103* - Internal Combustion Engines- Turbine

Citation Formats


                    Matta, R K, and Bhutiani, P K. Thrust reverser for high bypass turbofan engine.  United States: N. p., 1990. 
        Web.

Copy to clipboard


                    Matta, R K, & Bhutiani, P K. Thrust reverser for high bypass turbofan engine.  United States.

Copy to clipboard


                    Matta, R K, and Bhutiani, P K. 1990.  
        "Thrust reverser for high bypass turbofan engine".  United States.

Copy to clipboard


                    
@article{osti_6715238,

  title        = {Thrust reverser for high bypass turbofan engine},

  author       = {Matta, R K and Bhutiani, P K},

  abstractNote = {This patent describes a thrust reverser for a gas turbine engine of the type which includes an outer wall spaced from the center body of a core engine to define a bypass duct therebetween. The thrust reverser comprising: circumferentially displaced blocker doors, each of the doors being movable between a normal position generally aligned with the outer wall and a thrust reversing position extending transversely of the bypass duct for blocking the exhaust of air through the bypass duct and directing the air through an opening in the outer wall for thrust reversal; each of the blocker doors being of lightweight construction and including a pit in the inner surface thereof in the normal position; means for covering the pit during normal flow of air through the bypass duct to reduce the pressure drop in the bypass duct and to reduce noise. The covering means including a pit cover hingedly mounted at one end thereof on the blocker door and means of biasing the pit cover away from the blocker door to a position providing smooth flow of air through the bypass duct during normal operation.},

  doi          = {},

  url          = {https://www.osti.gov/biblio/6715238},
  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {Tue May 08 00:00:00 EDT 1990},

  month        = {Tue May 08 00:00:00 EDT 1990}

}

Copy to clipboard

Patent:

Search for the full text at the U.S. Patent and Trademark Office

Save / Share:

Export Metadata

Save to My Library

Similar records in OSTI.GOV collections:

Passive bypass valve assembly

Patent Siedlecki, Jr, W

This patent describes a bypass valve assembly for controlling fluid flow in a gas turbine engine. It comprises an annular frame including an outer casing, an inner casing spaced from the outer casing to define a channel for channeling fluid flow and the outer casing including an annular opening therein; a plurality of circumferentially juxtaposed bypass valve doors disposed in the annular opening, each of the valve doors having an inner surface for facing the fluid flowable in the channel, an outer surface, a first end pivotally connected to the frame, and a second end, the doors being positionable inmore »« less
Gas turbine engine with augmentor and variable area bypass injector

Patent Giffin, III, R; Woltmann, I; McHugh, D

This patent describes a gas turbine engine thrust for providing augmented thrust, comprising: (a) a plurality of circumferentially disposed hollow members positioned in the path of core gases from the core engine; (b) each of the members extending generally radially from the bypass duct to the center body; (c) each of the members being open at the radially outward end for receiving bypass gas from the bypass duct; (d) each of the members including spaced apart sidewalls and an opening in one of the side walls near the trailing edge and extending substantially the length of each of the membersmore »« less
Medium bypass turbofan engine

Patent Williams, S; Jones, J; Dorer, D

A gas turbine engine of the turbofan type is described which consists of: A. a generally tubular axially extending housing assembly defining a radially outer annular bypass duct extending from the inlet end of the housing assembly to the exhaust end thereof; B. an annular burner positioned within the housing assembly radially inwardly of the bypass duct and concentric to the central axis of the housing assembly; C. a low pressure spool assembly including a first shaft journaled on the central axis of the housing assembly, a fan on the first shaft disposed proximate the inlet end of the housingmore »« less
Combustion heated air turbine starter system

Patent Shekleton, J

This paper describes a combustion heated air turbine starter system. It comprises: an air turbine starter operatively associated with a main turbine engine; an auxiliary power unit adapted to deliver air through a bleed duct to the air turbine starter; and means for combusting fuel from a source with air from the auxiliary power unit; the combusting means including an auxiliary combustor disposed within the bleed duct upstream of the air turbine starter, the auxiliary combustor including an outer wall positioned in radially inwardly spaced relation to the bleed duct, the outer wall defining an axial combustion air flow pathmore »« less
Separable fan strut for a gas turbofan power plant

Patent Munroe, A; Blume, K; Gurney, R

An improved gas turbofan power plant of the type having an engine core circumferentially disposed about a longitudinal centerline, the engine core defining a primary flow passage having a radially inner flow surface, and a fan cowling circumferentially disposed outward of and concentric with the engine core to define a secondary flow passage therebetween, wherein the improvement is described comprising of: a plurality of through struts extending radially between the radially inner flow surface and the fan cowling, the plurality of struts joining the engine core and fan cowling and transferring the operational loads between the engine core and fanmore »« less

Similar Records