Abstract: The present disclosure relates to an airframe assembly comprising an airframe support structure defining an engine void and configured to support a gas turbine engine along an engine axis of the engine void; a thermal enclosure configured to surround the gas turbine within the engine void; a heat exchange channel formed between an outer flow-bounding wall of the engine void and an inner wall defined by the thermal enclosure, configured to convey a cooling flow through the engine void outside of the thermal enclosure for the gas turbine engine; and a heat exchanger mounted to the airframe support structure for heat exchange between the cooling flow and a working fluid provided to the heat exchanger.

Abstract: The present disclosure provides an accessory power module for a gas turbine engine having a high-pressure spool and a low-pressure spool, the accessory power module comprising: a first electrical machine configured to couple to the low-pressure spool of the gas turbine engine; a casing housing the first electrical machine, the casing comprising at least one support element configured to support the first electrical machine within the casing, wherein the casing is configured for airflow therethrough; an accessory gearbox comprising an input coupling configured to couple to the high-pressure spool of the gas turbine engine, the accessory gearbox mounted to the casing; and a second electrical machine configured to couple to an output coupling of the accessory gearbox; wherein the casing is configured to be mounted along an inlet air flow path into the gas turbine engine.

Abstract: The present disclosure provides a podded engine adaptor configured to secure a podded engine to an aircraft, comprising: an airframe mounting interface configured for attachment to an airframe of an aircraft; an engine mounting interface configured for attachment to an engine; wherein the podded engine adaptor is configured to be attached to an engine at the engine mounting interface and to an airframe of the aircraft at the airframe mounting interface, so as to indirectly couple an engine to the aircraft via the podded engine adaptor.

Abstract: The present disclosure relates to a hydraulic fuse comprising: a fuse body defining a plenum, the plenum comprising: an inlet configured to couple to a first fluid location; and an outlet configured to couple to a second fluid location.

Abstract: Disclosed is an aircraft accessory drive system comprising: a drive shaft configured to provide a drive input; a critical accessory directly coupled to the drive shaft so as to be directly driven by the drive shaft; a parasitic drive system configured to transmit drive input from the drive shaft to one or more less critical accessories, wherein the parasitic drive system comprises a torque limiter configured to decouple the parasitic drive system from the drive shaft and the critical accessory in response to a jam affecting the parasitic drive system or one or more of the less critical accessories. Also disclosed are a gas turbine engine comprising an aircraft accessory drive system, and an aircraft comprising an aircraft accessory drive system.

Abstract: Disclosed is an aircraft accessory drive system comprising: a drive shaft configured to provide a drive input; a critical accessory directly coupled to the drive shaft so as to be directly driven by the drive shaft; a parasitic drive system configured to transmit drive input from the drive shaft to one or more less critical accessories, wherein the parasitic drive system comprises a torque limiter configured to decouple the parasitic drive system from the drive shaft and the critical accessory in response to a jam affecting the parasitic drive system or one or more of the less critical accessories. Also disclosed are a gas turbine engine comprising an aircraft accessory drive system, and an aircraft comprising an aircraft accessory drive system.

Abstract: A tube gallery for a gas turbine engine includes a body. The body includes an external surface. The body also includes a plurality of channels defined in the body. Each channel includes an inlet disposed on the external surface, an outlet spaced apart from the inlet and disposed on the external surface, and a passage extending between and fluidly communicating the inlet to the outlet. The passage of each channel has a non-circular cross-sectional shape. The non-circular cross-sectional shape has a first maximum dimension along a first direction and a second maximum dimension along a second direction orthogonal to the first direction. The first maximum dimension is greater than the second maximum dimension by a factor of at least 1.2.

Abstract: A tube gallery for a gas turbine engine includes a body. The body includes an external surface. The body also includes a plurality of channels defined in the body. Each channel includes an inlet disposed on the external surface, an outlet spaced apart from the inlet and disposed on the external surface, and a passage extending between and fluidly communicating the inlet to the outlet. The passage of each channel has a non-circular cross-sectional shape. The non-circular cross-sectional shape has a first maximum dimension along a first direction and a second maximum dimension along a second direction orthogonal to the first direction. The first maximum dimension is greater than the second maximum dimension by a factor of at least 1.2.

Abstract: An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.

Abstract: An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.

Abstract: A gimbal expansion joint includes a first clevis adapted to be secured to one end of a first piece of ducting, a second clevis adapted to be secured to an end of a second piece of ducting, and a gimbal arrangement to which the first and second clevises are pivotably connected to form a universal joint between the ends of the pieces of ducting. A flexible duct extends between the first and second clevises to form a passage for fluid communication between the ends of the first and second pieces of ducting. The flexible duct has a respective flange at each end, each flange providing an axially-directed face across which a clamping load is applied to affix the flange to a corresponding axially-directed face of the respective clevis.

Abstract: The present invention provides a gimbal expansion joint for use in joining ducting. The gimbal expansion joint has a first clevis adapted to be secured to one end of a first piece of ducting, a second clevis adapted to be secured to an end of a second piece of ducting, and a gimbal arrangement to which the first and second devises are pivotably connected to form a universal joint between the ends of the pieces of ducting. The joint further has a flexible duct extending between the first and second clevises to form a passage for fluid communication between the ends of the first and second pieces of ducting. The flexible duct has a respective flange at each end. Each flange provides an axially-directed face across which a clamping load is applied to affix the flange to a corresponding axially-directed face of the respective clevis.