Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.

Abstract: A method includes providing an exhaust liner as a first duct, providing a second duct having an opening therein, and spacing the first duct radially inward of the second duct. A spring connects the first and second ducts together and has first and second ends. A first mount comprises a first bracket portion associated with the spring and a second bracket portion directly fixed to the first duct. The first bracket portion is directly fixed to the first end of the spring and the second end of the spring is fixed to a second mount that comprises a casing plate having an area greater than the opening. The first end of the spring and the first bracket portion are inserted through the opening and the first bracket portion is attached to the second bracket portion. The casing plate is directly fixed to a radially outward facing surface of the second duct.

Abstract: A method includes providing an exhaust liner as a first duct, providing a second duct having an opening therein, and spacing the first duct radially inward of the second duct. A spring connects the first and second ducts together and has first and second ends. A first mount comprises a first bracket portion associated with the spring and a second bracket portion directly fixed to the first duct. The first bracket portion is directly fixed to the first end of the spring and the second end of the spring is fixed to a second mount that comprises a casing plate having an area greater than the opening. The first end of the spring and the first bracket portion are inserted through the opening and the first bracket portion is attached to the second bracket portion. The casing plate is directly fixed to a radially outward facing surface of the second duct.

Abstract: A hanger assembly for use between a first duct and a second duct having an opening therein includes a spring having a first end and a second end, a first mount for attaching the first end to the first duct, a second mount for attaching the second end to the second duct, the second mount having an area greater than the opening, and a central aperture therethrough.

Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.

Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first attachment member including an opening, a second attachment member including a loop at least partially extending through the opening, and a pin between the first attachment member and the loop.

Abstract: A push-lock pin for connecting a tile to a gas turbine engine wall according to an exemplary aspect of the present disclosure includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including a push-down pop-up mechanism and a locking mechanism, the locking mechanism moveable to a locked position such that the locking mechanism limits movement of a tile away from a gas turbine engine wall; and a stop feature to limit movement of the tile toward the gas turbine engine wall.

Abstract: A push-lock device for connecting a tile to a gas turbine engine wall includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including portions of both a push-down pop-up mechanism and a locking-bracket mechanism, the locking-bracket mechanism moveable to a locked position such that the locking-bracket mechanism limits movement of a tile away from a gas turbine engine wall; and a biasing member to be positioned closer to the tile than the locking-bracket mechanism.

Abstract: A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass. The flow control translates axially between an open position and a closed position to vary and control airflow through the second bypass passage.

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first attachment member including an opening, a second attachment member including a loop at least partially extending through the opening, and a pin between the first attachment member and the loop.

Abstract: A support hanger is provided for a turbine engine. The support hanger includes a pin with a pin head, a retainer and a flexible seal. The retainer is pivotally connected to the pin head. The retainer includes a seal bearing surface facing towards the pin head. The seal includes a retainer bearing surface sealingly engaging the seal bearing surface.

Abstract: A turbine engine case includes a first panel, a second panel and a support hanger. The second panel defines an aperture. The support hanger includes a strut that is connected to the first panel, and a base that is pivotally connected to the strut. The base includes a pivot member that is pivotally engaged with the second panel. The base extends away from the strut and through the aperture to the pivot member.

Abstract: A gas turbine engine includes a bypass flowpath between an outer engine case structure and a core engine. The bypass flow exits the engine through a nozzle. A flow control device that can expand or contract is arranged around the nozzle to control the bypass flow and includes a plurality of overlapping arcuate segments. A method of controlling a bypass flow includes providing a flow control device with overlapping segments that defines a bypass flow path, and actuating the segments to change the amount of overlap between segments and therefore the size of the bypass flow path.

Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.

Abstract: A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass. The flow control translates axially between an open position and a closed position to vary and control airflow through the second bypass passage.

Abstract: A push-lock pin for connecting a tile to a gas turbine engine wall according to an exemplary aspect of the present disclosure includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including a push-down pop-up mechanism and a locking mechanism, the locking mechanism moveable to a locked position such that the locking mechanism limits movement of a tile away from a gas turbine engine wall; and a stop feature to limit movement of the tile toward the gas turbine engine wall.

Abstract: A push-lock device for connecting a tile to a gas turbine engine wall includes, among other things, a housing extending longitudinally along an axis; a shaft assembly within the housing, the shaft assembly including portions of both a push-down pop-up mechanism and a locking-bracket mechanism, the locking-bracket mechanism moveable to a locked position such that the locking-bracket mechanism limits movement of a tile away from a gas turbine engine wall; and a biasing member to be positioned closer to the tile than the locking-bracket mechanism.

Abstract: A gas turbine engine includes a fan section and an intercooling turbine section along an engine axis aft of a fan section and forward of a combustor section.

Abstract: A hanger assembly for use between a first duct and a second duct having an opening therein includes a spring having a first end and a second end, a first mount for attaching the first end to the first duct, a second mount for attaching the second end to the second duct, the second mount having an area greater than the opening, and a central aperture therethrough.