A turbine support assembly includes a turbine rotor joined to a fan shaft through a support shaft. The support shaft is joined to the fan shaft in a V-configuration having first and second legs joined together at an apex and inclined axially apart, with at least the first leg forming an integral part of the fan shaft. The second leg is rotatably supportable to a frame. The V-configuration increases the stiffness of the turbine support to reduce blade tip clearances. The present invention also provides an annular integral bolt heat shield and axial retention apparatus to axially retain bolts used for holding together two rotor elements during assembly when the bolts are otherwise subject to sliding into a closed cavity of the assembled engine or one of its modules. The integral retainer and heat shield engage the bolts disposed through bolt holes in a gas turbine engine rotor shaft so that the bolts remain straight during assembly when a second rotor element such as a second shaft is being attached to the first shaft, and bolt holes in the second shaft have to engage and fit over the bolts of the first shaft. One particular embodiment of the present invention provides a low pressure turbine rotor shaft assembly of a low pressure turbine module wherein forward and aft shafts are attached by bolts which have bolt heads in a closed cavity of the module and are slidably disposed through corresponding bolt holes of each shaft such that the bolt heads are disposed aft of the aft shaft. An integral heat shield and axial bolt retainer is mounted to the aft shaft aft of the bolt heads so as to trap and retain the bolt heads between the shield and the aft shaft.

Turbine support assembly including turbine heat shield and bolt retainer assembly

An emergency electrical power generating apparatus (50) for use with a turbofan engine comprises an electrical generator (52) and a clutch assembly (54). The clutch assembly (54) connects the electrical generator (52) with a fan assembly (1) of the engine only during a windmill action of the fan assembly (1). The electric generator (52) having a stator (82) mounted to a housing (86) of a bearing (88) and a rotor (84) mounted to one of a fan shaft (90) and a low pressure spool shaft (17), supported directly on the bearing (88).

Fan driven emergency generator

A variable cycle turbofan engine includes first and second fans independently joined to respective turbines. A first bypass duct surrounds a core engine disposed in flow communication with the second fan. A second bypass duct surrounds the first bypass duct in flow communication with the first fan. A first exhaust nozzle is joined to both the core engine and first bypass duct. And, a second exhaust nozzle is joined to the second bypass duct.

Double bypass turbofan

A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A thrust vectoring system is joined between a compressor and the nozzle. A controller is operatively joined to the thrust vectoring system for selectively varying distribution of air bled from the compressor into the exhaust nozzle for vectoring propulsion thrust.

Thrust vectoring missile turbojet

A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. An integral starter-generator is disposed inside the core engine and is joined to the rotor for equal speed rotation therewith. An electrical controller coordinates operation of the engine for subsonic, transonic, and supersonic operation of the engine in a missile self-powered by the starter-generator.

Self powdered missile turbojet

A gas turbine engine of the free power turbine type, in which the power turbine rotates independently of the compressor driving turbine, is provided with conversion means for coupling and decoupling the power turbine from the compressor driving turbine. In the uncoupled mode of operation, the powerplant and its associated load may be quickly accelerated to operating speed with a minimum of externally applied starting torque and energy. Once operating speed is attained, the power turbine may be coupled to the compressor driving turbine in order that transient speed changes of the gas turbine engine in response to changes in the load requirement be maintained at a minimum.

Conversion means for a gas turbine engine

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Conversion means for a gas turbine engine