Abstract: The weight of a high pressure storage vessel 20 for an oxidant used to oxidize fuel in a combustor 12 which in turn provides gases of combustion to a turbine wheel 10 may be minimized by providing an incendiary device 32 within the vessel 20 which is triggered by a sensor 34, 36 in response to some sensed characteristic of the oxidant within the vessel 20 to increase the pressure within the vessel 20 and to drive the oxidant to the combustor 12.

Abstract: Improved starting for turbine engines operating at low fuel flows and at high altitudes is accomplished in an engine 10 having an annular combustion 12 by utilizing a stored energy combustion system 28 which includes a source of oxidant 36 and a fuel source 38 both of which are in fluid communication with an auxiliary combustion space 32 of an auxiliary combustor 30 for combusting the oxidant and fuel to generate a gaseous fuel including secondary gases of combustion which are directed to the annular combustor 12 through a fuel injector 24 as a reactive, gaseous fuel ignitable therewithin.

Abstract: The problem of excessive weight in an aircraft 10 powered by at least one turbine engine 12 as a result of the incorporation of both a starter for the turbine engine 12 and a source of emergency power is avoided by utilizing a turbine wheel 62 to alternatively start the engine 12 or drive an emergency power generator 102. The turbine wheel 62 may be driven either by compressed air from a ground source 34 or an engine bleed 32 or, in the alternative, by hot gases of combustion from a stored energy source 36 in an emergency situation.

Abstract: The weight of a high pressure storage vessel 20 for an oxidant used to oxidize fuel in a combustor 12 which in turn provides gases of combustion to a turbine wheel 10 may be minimized by providing an incendiary device 32 within the vessel 20 which is triggered by a sensor 34, 36 in response to some sensed characteristic of the oxidant within the vessel 20 to increase the pressure within the vessel 20 and to drive the oxidant to the combustor 12.

Abstract: A guide vane assembly for controllably varying fluid mass flow rates past compressor blades in an auxiliary power unit. The auxiliary power unit comprises a rotary apparatus for compressing fluid in a compressor housing wherein a plurality of compressor blades are mounted on a rotating hub. A fluid flow path extends through the housing which has a duct portion extending upstream of the compressor blades to an inlet plenum to define at least a portion of the fluid flow path. The guide vane assembly includes a central gear box adjacent the compressor housing which has a ring gear mounted for limited rotational movement. A plurality of guide vanes are disposed in the duct portion of the housing and are mounted for pivotal movement responsive to rotational movement of the ring gear. The guide vane assembly is adapted to convert rotation of the ring gear to pivotal movement of the guide vanes.

Abstract: Weight and spatial concerns in aircraft are alleviated or minimized through a combined auxiliary and emergency power unit including a gear box 10 adapted to drive a generator 16 and a hydraulic pump 18 as auxiliary to emergency power supplies for the aircraft. The system includes a pair of turbine wheels 22 and 24 along with a pair of motion transmitting paths 12, 26, 42; 14, 68, each including a selectively operable clutch 42, 68 so as to connect the turbine wheels 22, 24 to the gear box 10 in mechanical parallel. A rotary compressor 28 is connected to one of the turbine wheels 22 and an associated combustor 46 provides combustion gas to the turbine wheel 22 for auxiliary power unit operation. A pressure tank 56 for compressed oxidant and an additional combustor 60 are utilized to provide combustion gas to the other turbine wheel 24 in an emergency power unit mode of operation.

Abstract: An enriched oxidant for use with an air breathing turbine engine driven power unit 14 in abnormal operating conditions may be obtained from an oxygen enriched air outlet 30 of a conventional inert gas generator 24 employed for providing nitrogen enriched air to "inert" aircraft fuel tanks 12.

Abstract: Duplication of engine and secondary power system components in individual auxiliary and emergency power units is avoided in an integrated power unit including a gas turbine engine 10 having a centrifugal compressor 28 and a turbine 40, a generator 18 coupled to the engine 10, an air inlet 22 to the compressor 28, a first reservoir 82 for combustible fuel, and a first combustor 34, 36 for receiving and combusting compressed air from the compressor 28 and fuel from the reservoir 82 to generate gases of combustion and feeding the gases of combustion to the turbine 40 by the provision of a second reservoir 80 for containing a compressed oxidant for combusting fuel from the first reservoir 82, a second combustor 48 for receiving and combusting fuel from the first reservoir 82 and oxidant from the second reservoir 80 to generate gases of combustion, flow paths 64, 66, 68 for introducing fuel from the reservoir 82 into the gases of combustion from the second combustor 48 to vaporize the fuel and a conduit 50, 52 for

Abstract: Duplication of engine and secondary power system components in individual auxiliary and emergency power units is avoided in an integrated power unit including a gas turbine engine 10 having a centrifugal compressor 28 and a turbine 40, a generator 18 coupled to the engine 10, an air inlet 22 to the compressor 28, a first reservoir 82 for combustible fuel, and a first combustor 34, 36 for receiving and combusting compressed air from the compressor 28 and fuel from the reservoir 82 to generate gasses of combustion and feeding the gasses of combustion to the turbine 40 by the provision of a second reservoir 80 for containing a compressed oxidant for combusting fuel from the first reservoir 82, a second combustor 48 for receiving and combusting fuel from the first reservoir 82 and oxidant from the second reservoir 80 to generate gasses of combustion, flow paths 64, 66, 68 for introducing fuel from the reservoir 82 into the gases of combustion from the second combustor 49 to vaporize the fuel and a conduit 50, 52