Sundstrand Corporation

Hamilton Sundstrand Corporation

Robert W Smith

Jack R Shekleton

Roy W Vershure, Jr

Anthony C Jones

Steven W Lampe

Jeremy J Walters

Jack R Shekelton

Steve Heitz

A compressor bleed air valve in an auxiliary power unit ('APU') modulates bleed air flow both for accessory pneumatic systems powered by the bleed air and for reducing or removing surge in the compressor.

APU bleed valve with integral anti-surge port

A hot gas generator includes a dual fuel injector (42) having spaced fuel discharge nozzles (48, 60) on the longitudinal axis (28) of a vessel (18) having a narrow inlet (22), an opposite narrow outlet (14) and an intermediate, enlarged chamber (24) which serves as a combustion chamber. The nozzle (60) injects a spray cone (64) of fuel in a cone angle that is sufficiently wide that a large angle exists between the fuel spray and the path (54) of high velocity combustion gases moving toward the outlet (14) to achieve excellent vaporization of fuel at fuel rich conditions without causing carbon buildup and/or the generation of black smoke in the exhaust.

Staged, coaxial, multiple point fuel injection in a hot gas generator

Difficulties with fuel atomization at low fuel flow rates in gas turbine fuel injection systems may be overcome by use of an impingement injector (52) including a cylindrical orifice (64, 94, 114) that is smooth, straight and uninterrupted by burrs or other disturbances having an exit opening (68, 96, 118) transverse to the axis of the orifice (64, 94, 114) and facing an impingement surface (72, 101, 126) that is planar and spaced from the exit opening (68, 96, 118).

Fuel injector for a gas turbine engine

Difficulties with starting reliability and/or combustion stability in hot gas generating systems are avoided in a construction including a storage vessel (36) for storing an oxidant, a fuel supply (22) and combustion chamber (26) having an out outlet (30) for hot gas. A fuel injection nozzle (28) provides fuel from the supply (22) to the combustion chamber (26) while an oxidant duct (44) connects the vessel (36) to the combustion chamber (26). A choked orifice (46) is disposed in the duct (44) just upstream of the combustion chamber (26) and a bypass duct (50) interconnects the combustion chamber outlet (30) and the oxidant duct (44) between the choke orifice (46) and the combustion chamber (26). A selectively operable valve (53) is disposed in the bypass duct (50) and a pressure regulator (44) is disposed in the oxidant duct (44) for selectively controlling the pressure of oxidant applied to the choked orifice (46).

Stored energy, wide energy range turbine starting engine

In order to control engine operation by exhaust gas measurement, while avoiding operating conditions that exceed the safe maximum temperature limit, a gas turbine engine (10) includes a thermocouple temperature probe (28). The gas turbine engine (10) has a rotary compressor (12), a turbine wheel (14) coupled to the compressor (12) for driven movement thereof, and an annular nozzle (16) proximate the turbine wheel (14) for directing gases of combustion at the turbine wheel (14). It also includes an annular combustor (18) defining an annular combustion space (20) disposed about the turbine wheel (14) and in fluid communication with both the compressor (12) and the nozzle (16). The combustor (18) receives fuel from a source and air from the compressor (12) and it combusts fuel and air in the combustion space (20) to generate the gases of combustion. It further includes an exhaust duct (22) leading from the turbine wheel (14) for exhausting the gases of combustion generated in the combustion space (20) after the gases of combustion have been directed at the turbine wheel (14) by the annular nozzle (16). The exhaust duct (22) directs the gases of combustion axially away from the turbine wheel (14) substantially centered about a centerline (26) thereof. With this arrangement, the thermocouple temperature probe (28) is adapted to measure a mean temperature for the gases of combustion substantially at the centerline of the exhaust duct (22).

Turbine temperature exhaust monitoring system

In order to optimize ignition capabilities, while at the same time enhancing the life span of an igniter, a stored energy combustor (10) has an igniter (34) disposed within a fuel injector (26). The fuel injector (26) is disposed in a tubular extension (16) leading to a combustion chamber (20) and has a discharge end (28) communicating with a point of entry into the combustion chamber (20). An oxidant inlet port (24) is provided upstream of the combustion chamber (20) for directing oxidant into the combustion chamber (20). The oxidant inlet port (24) directs oxidant through the tubular extension (16) leading to the combustion chamber (20) in surrounding relation to the fuel injector (26). With this arrangement, the igniter (34) is disposed within the fuel injector (26) along a longitudinal axis (22) of the stored energy combustor (10).

Stored energy combustor with fuel injector containing igniter means for

Difficulties with starting reliability and/or combustion stability in hot gas generating systems are avoided in a construction including a storage vessel (36) for storing an oxidant; a fuel supply (22) and a combustion chamber (26) having an outlet (30) for hot gas. A fuel injection nozzle (28) provides fuel from the supply (22) to the combustion chamber (26) while an oxidant duct (44) connects the vessel (36) to the combustion chamber (26). A choked orifice (46) is disposed in the duct (44) just upstream of the combustion chamber (26) and a bypass duct (50) interconnects the combustion chamber outlet (30) and the oxidant duct (44) between the choked orifice (46) and the combustion chamber (26). A selectively operable valve (53) is disposed in the bypass duct (50) and a pressure regulator (42) is disposed in the oxidant duct (44) for selectively controlling the pressure of oxidant applied to the choked orifice (46).

Stored energy, wide energy range turbine starting system

Difficulties in accommodating thermal growth in a combustor for providing hot gases of combustor to drive, for example, a turbine wheel (10) are avoided in a combustor construction, including a housing (36) defining a combustion chamber having a relatively narrow inlet (38), an enlarged combustion area (42) and a relatively narrow outlet (40) opposite of the inlet (38). A fuel injector (46) is disposed in the inlet (38) for injecting fuel (50) at least into the combustion area (42) and a plenum case (56) surrounds the housing (36) in generally spaced relation. The plenum case (56) is adapted to be connected to a source (62) of oxidant under pressure and is in fluid communication with the inlet (38) to provide oxidant thereto to support combustion of fuel in the combustion area (42). A conduit (44) extends from the outlet (40) to be connected to a turbine nozzle (16) and a diaphragm (122) is interposed and sealingly engages both the housing (36) and the plenum case (56) near the outlet (40). A first labyrinth seal (116) is located on one side of the diaphragm (122) and between the housing (36) and the plenum case (56) while a second labyrinth seal (104) is located on the other side of the diaphragm (122) and is disposed between the plenum case (56) and the conduit (44).

Seal for a stored energy combustor

In order to significantly reduce the carbon produced in a combustor, and thus reduce or eliminate carbon buildup on a combustor wall (14), a stored energy combustor (10) has a fuel injector (28) in a tubular extension (16) of a vessel (12) leading to a combustion chamber (20). The fuel injector (28) has a discharge end (60) upstream of a plane defining a point of entry (32) into the combustion chamber (20) for directing an annulus of fuel (26) toward the combustion chamber (20), and an oxidant inlet port (24) is also provided upstream of the combustion chamber (20) for directing oxidant into the combustion chamber (20) through the tubular extension (16) in surrounding relation to the fuel injector (28) which is concentric with the longitudinal axis (22) of the vessel (12). In addition, the stored energy combustor (10) includes an air swirler (34) upstream of the combustion chamber (20) and the discharge end ( 60) of the fuel injector (28) for swirling oxidant in the tubular extension (16) which directs oxidant in a swirling annulus (46) into the combustion chamber (20) outwardly of the annulus of fuel (26).

Stored energy combustor

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.

Gas turbine engine stored energy combustion system

Improved performance in a hot gas generator 10 is achieved by providing a liner 21 positioned within a wall 14 of a vessel 12 so as to be disposed about a combustion chamber 20 therein. The liner 21 is positioned relative to the wall 14 to define a relatively uniform gap 26 therebetween and is adapted to thermally expand under heat for controlling heat transfer from the combustion chamber 20 through the liner 21 and the wall 14 entirely throughout a preselected temperature range. With this arrangement, the gap 26 is selected to accommodate thermal expansion of the liner 21 in a manner producing relatively little stress thereon.

Hot gas generator

In order to avoid carbon buildup and to assist fuel atomization, a fuel injection system (40) includes a fuel injector (42) associated with the upstream portion (44) of a combustor (10). The fuel injector (42) has a fuel flow passage (46) in communication with a source of fuel (14) and terminating in the upstream portion (44) of the combustor (10). The fuel injection system (40) also includes a primary oxidant delivery tube (20) associated with the upstream portion (44) of the combustor (10). The primary oxidant delivery tube (20) defines a primary oxidant flow passage (48) in communication with a source of oxidant (12) and terminating in the upstream portion (44) of the combustor (10). The fuel injection system (40) further includes a secondary oxidant delivery tube (50) associated with the upstream portion (44) of the conbustor (10). The secondary ocidant delivery tube (50) defines a secondary oxidant flow passage (52) in communication with the source of oxidant (12) and terminating in the upstream portion (44) of the combustor (10). The fuel injection system (44) is such that the fuel flow passage (46) is adapted to inject fuel from the source (14) into the upstream portion (44) of the combustor (10). The primary and secondary oxidant flow passages (48 and 52) are then adapted to deliver oxidant from the source (12) into the upstream portion (44) of the combustor (10) in surrounding relation to fuel injected through the fuel flow passage (46). With this arrangement, the secondary oxidant flow passage (52) is designed to assist in atomizing fuel injecting through the fuel flow passage (46) in a manner avoiding carbon buildup in the combustor (10).

Stored energy combustor fuel injection system

A spray nozzle including a body having a fluid inlet at one end thereof and an exit orifice at the other end thereof. The fluid inlet communicates with the exit orifice through a fluid flow path extending through the body. The exit orifice is adapted to atomize the fluid as the fluid leaves the body. The spray nozzle also includes a separate portion for atomizing the fluid independent of the exit orifice. The separate portion communicates with the fluid flow path upstream of the exit orifice. The separate portion produces a flat spray of the fluid as the fluid leaves the body. With these features, the spray nozzle is well suited as a fuel injector for a gas turbine.

Spray nozzle

Improved performance in a hot gas generator 10 is achieved by providing a pair of hemispherical liners 22 and 24 loosely positioned within an interior wall 14 of a vessel 12 so as to be disposed above a combustion chamber 20 therein. The hemispherical liners 22 and 24 normally have a groove 26 at an interface therebetween and are formed of a material adapted to thermally expand under heat. Specifically, the hemispherical liners 22 and 24 expand to close the groove 26 at the interface in a manner producing relatively little stress thereon.

Improved performance in a hot gas generator is achieved by disposing a multiple port fuel injector 42 having three spaced fuel discharge ports 46, 48, 49 on the longitudinal axis 28 of a vessel 18 having a narrow inlet 22, an opposite narrow outlet 14 and an intermediate, enlarged chamber 24 which serves as a combustion chamber.

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Lakeside, CA, United States of America

Robert W Smith