TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE

To provide a turbine engine with a single wall cantilevered architecture.SOLUTION: An apparatus and method for mounting a turbine engine (20) to an aircraft (10) can include an engine core (40) for the turbine engine (20) including a compressor section (42), a combustor section (48), and a turbine s...

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Main Authors GOULD KENNETH A, MARTIN MILES D'ANGELO, MARK GREGORY WOTZAK, BRIAN LEWIS DEVENDORF, DANIEL WASLO
Format Patent
LanguageEnglish
Japanese
Published 22.03.2019
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:To provide a turbine engine with a single wall cantilevered architecture.SOLUTION: An apparatus and method for mounting a turbine engine (20) to an aircraft (10) can include an engine core (40) for the turbine engine (20) including a compressor section (42), a combustor section (48), and a turbine section (52) in flow arrangement. At least one strut (110) couples to the engine core (40) at a single mount plane (120). A structural wall (116) at least partially defining a mainstream flow path (118) couples to the at least one strut (110) and passes through the compressor section (42) and the turbine section (52).SELECTED DRAWING: Figure 2 【課題】単一壁片持ち構造を有するタービンエンジンを提供する。【解決手段】タービンエンジン（２０）を航空機（１０）に取り付けるための装置および方法が、圧縮機部分（４２）と、燃焼器部分（４８）と、タービン部分（５２）とを流れの配置にて含むタービンエンジン（２０）のためのエンジンコア（４０）を含むことができる。少なくとも１つの支柱（１１０）が、単一の取り付け平面（１２０）においてエンジンコア（４０）に結合する。主流路（１１８）を少なくとも部分的に定める構造壁（１１６）が、少なくとも１つの支柱（１１０）に結合し、圧縮機部分（４２）およびタービン部分（５２）を通過する。【選択図】図２
Bibliography:Application Number: JP20180152835