TURBINE ENGINE WITH SINGLE WALL CANTILEVERED ARCHITECTURE

• Main Authors: DEVENDORF BRIAN LEWIS, WASLO DANIEL, D'ANGELO MARTIN MILES, GOULD KENNETH ARTHUR, WOTZAK MARK GREGORY
• Format: Patent
• Language: Chinese; English
• Published: 05.03.2019
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; AIRCRAFT; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT; AVIATION; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; COSMONAUTICS; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MECHANICAL ENGINEERING; PARACHUTES; PERFORMING OPERATIONS; TRANSPORTING; WEAPONS

The invention provides an apparatus and a method for mounting a turbine engine to an aircraft. The apparatus can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section. 种用于将涡轮发动机安装到飞行器上的设备及方法，可包括用于涡轮发动机的发动机核心，其包括以流动顺序布置的压缩机区段、燃烧器区段和涡轮区段。至少个支柱围绕单个安装平面耦接到发动机核心上。至少部分地限定主流流径的结构壁耦接到至少个支柱上，且穿过压缩机区段和涡轮区段。