Abstract: A turbomachine frame member including an annular inner hub and a concentric annular outer casing that is spaced radially outwardly from the inner hub to define an annular flow passageway. A plurality of substantially radially-extending, circumferentially-spaced struts interconnect the inner hub and outer casing. The struts are connected to the outer casing by respective pairs of connecting bolts that pass through the outer casing and into the struts to engage barrel nuts.

Abstract: A turbomachine frame member including an annular inner hub and a concentric annular outer casing that is spaced radially outwardly from the inner hub to define an annular flow passageway. A plurality of substantially radially-extending, circumferentially-spaced struts interconnect the inner hub and outer casing. The struts are connected to the outer casing by respective pairs of connecting bolts that pass through the outer casing and into the struts to engage barrel nuts.

Abstract: An annular hanger for supporting an annular wall element from a gas turbine engine annular outer casing is circumscribed about a centerline extending in opposite first and second axial directions and has an annular first hook extending in the first axial direction from said body section and an annular second hook extending in the second axial direction. One of the hooks has circumferentially spaced apart tabs extending equal axial lengths from the body section and corresponding notches circumferentially disposed between a corresponding adjacent pair of the tabs. The annular hanger is used to support at least in part a wall element from the outer casing as part of a bayonet mount. The bayonet mount further includes a bayonet slot on one of the casing and the wall element and the hanger tabs are received within the bayonet slot.

Abstract: An annular hanger for supporting an annular wall element from a gas turbine engine annular outer casing is circumscribed about a centerline extending in opposite first and second axial directions and has an annular first hook extending in the first axial direction from said body section and an annular second hook extending in the second axial direction. One of the hooks has circumferentially spaced apart tabs extending equal axial lengths from the body section and corresponding notches circumferentially disposed between a corresponding adjacent pair of the tabs. The annular hanger is used to support at least in part a wall element from the outer casing as part of a bayonet mount. The bayonet mount further includes a bayonet slot on one of the casing and the wall element and the hanger tabs are received within the bayonet slot.

Abstract: A combustor apparatus is provided for a gas turbine engine including a circumferential ring of injectors. A fuel manifold provides a source of fuel for the injectors. The combustor apparatus includes a plurality of first fuel flow paths between the manifold and all of the injectors. Fuel is provided to all of the injectors via these first flow paths. At least one second fuel flow path including an electronically switchable valve is coupled between the manifold and a selected one of the injectors to provide additional fuel thereto at certain times when special engine operating conditions, such as demand for initial ignition, crossfire and altitude relight are sensed.