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Emlyn Jones, Richard G Stretton: Aeroengine nacelle. Rolls-Royce, W Warren Taltavull, Manelli Denison & Selter PLLC, August 15, 2006: US07090165 (39 worldwide citation)

A nacelle (55) for a gas turbine engine (10), the engine (10) comprising accessories (34) mounted to a fan casing (28) and a core engine (9), the nacelle (55) substantially surrounds the engine (10) and comprises an intake (12) and a thrust reverser unit (31). The thrust reverser unit (31) is formed ...


2
Richard G Stretton: Engine core stand arrangement and method of removal and transportation of an engine core. Rolls-Royce, Oliff & Berridge, August 10, 2010: US07770292 (21 worldwide citation)

Transportation of larger diameter gas turbine engines can be problematic. In such circumstances it is known to separate the fan assembly (30) from the engine core (1) and other parts to facilitate transportation. Separation of the fan assembly (30) and engine core (1) can require a gantry which adds ...


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Richard G Stretton, Martyn Richards: Heat exchanger arrangement. Rolls-Royce, Jeffrey S Melcher, Manelli Denison & Selter PLLC, October 12, 2010: US07810312 (20 worldwide citation)

In certain circumstances recovery of a fluid flow presented through a heat exchanger into another flow can create problems with respect to drag and loss of thrust. In gas turbine engines heat exchangers are utilized for providing cooling of other flows such as in relation to compressor air taken fro ...


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Richard G Stretton, Pawel R Zakrzewski: Gas turbine engine. Rolls-Royce, Jeffrey S Melcher, Manelli Denison & Selter PLLC, February 15, 2011: US07886520 (16 worldwide citation)

Within a turbine engine a heat exchanger may be provided to cool compressor air flows to be utilized for cabin ventilation or other functions. A fluid flow acting as a coolant for the heat exchanger is generally drawn from the by-pass duct of the engine and a dedicated outlet duct is provided such t ...


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Kenneth F Udall, Richard G Stretton: Engine mounting assembly. Rolls-Royce, Jeffrey S Melcher, Manelli Denison & Selter PLLC, October 5, 2010: US07806363 (15 worldwide citation)

An engine mounting assembly for an engine, e.g. a gas turbine engine comprises a plurality of carrying arrangements. Each carrying arrangement comprises a rear load absorbing assembly. Each load absorbing assembly provides a rear mounting point for an engine carrier. Each carrying arrangement furthe ...


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Richard G Stretton: Aircraft engine arrangement. Rolls-Royce, W Warren Taltavull, Manelli Dension & Selter & PLLC, February 3, 2009: US07484354 (12 worldwide citation)

In order to avoid external bulging (5) to accommodate accessory mechanisms (27) and gearboxes (30) to drive these mechanisms (27) in accordance with the present invention splitter fairings (26) are located within a bypass duct (23) of an engine (20). The bypass duct (23) is defined between a casing ...


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Richard G Stretton: Liner for a gas turbine engine casing. Rolls-Royce, W Warren Taltavull, Manelli Denison & Selter PLLC, August 14, 2007: US07255528 (12 worldwide citation)

A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing ...


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Richard G Stretton, Kenneth F Udall: Cowl structure for a gas turbine engine. Rolls-Royce, W Warren Taltavull, Manelli Denison & Selter PLLC, August 8, 2006: US07086219 (10 worldwide citation)

A cowl structure (18) for a gas turbine engine (10) comprises an outer skin (26) defining a first path for a load applied to the engine (10). The cowl structure (18) includes an inner skin (24) defining a second path for the load. The inner and outer skins (24, 26) are constructed such that a major ...