Abstract: A fuel injection system for a gas trubine engine combustion chamber comprises at least one pilot fuel injector having a fuel discharge passage communicated to the combustion chamber and at least one secondary fuel injector having a fuel discharge passage communicated to the combustion chamber and a fuel purging passage communicated to a higher pressure region upstream of the combustion chamber. A fuel flow control device supplies metered fuel flow to the pilot fuel injector under all regimes of engine operation and to the secondary fuel injector under certain, intermittent regimes of engine operation requiring fuel flow above a selected level. A shuttle valve is movable to a first position to provide fuel flow communication between the fuel control device and the fuel discharge passage of the secondary fuel injector for fuel injection to the combustion chamber.

Abstract: A fuel injection system for a gas turbine engine combustion chamber comprises at least one pilot fuel injector having a fuel discharge passage communicated to the combustion chamber and at least one secondary fuel injector having a fuel discharge passage communicated to the combustion chamber and a fuel purging passage communicated to a higher pressure region upstream of the combustion chamber. A fuel flow control device supplies metered fuel flow to the pilot fuel injector under all regimes of engine operation and to the secondary fuel injector under certain, intermittent regimes of engine operation requiring fuel flow above a selected level. A shuttle valve is movable to a first position to provide fuel flow communication between the fuel control device and the fuel discharge passage of the secondary fuel injector for fuel injection to the combustion chamber.

Abstract: An improved airblast fuel injector for a gas turbine engine wherein the injector comprises an inner air discharge chamber, a first fuel discharge chamber disposed outboard of the inner air chamber, an intermediate air discharge chamber disposed radially outboard of the first fuel chamber, a second fuel discharge chamber disposed radially outboard of the first outer air chamber, and an outer air discharge chamber disposed radially outboard of the second fuel chamber. The fuel flow from the first fuel discharge chamber is subjected to inner and outer atomizing air flows from the inner and intermediate air chambers. The fuel flow from the second fuel discharge chamber is subjected to inner and outer atomizing airflows from the intermediate and outer air discharge chambers. The individual fuel flow streams discharged from the first and second fuel discharge chambers provide an aggregate, high mass flow of fuel necessary for engine operation.

Abstract: Apparatus for cleaning an internal passage of an article, such as a fuel passage of a gas turbine or other engine. The apparatus comprises a container for containing cleaning fluid, means for communicating a first end of the passage to the cleaning fluid in the container, and cleaning fluid conduit means communicated to a second end of the passage in a manner to draw cleaning fluid from the container to flow through the passage from the first end toward the second end in response to flow of cleaning fluid through the conduit means. The apparatus includes means for blocking flow of cleaning fluid through the conduit means so as to direct the cleaning fluid therein to flow through the passage from the second end toward the first end and into the container.

Abstract: A self-purging fuel injector for a combustor of a gas turbine engine wherein the fuel injector comprises an injector body having first and second air discharge orifices for discharging air to the combustor and first and second fuel passage means having respective first and second fuel discharge orifices for discharging fuel to the combustor. The first and second fuel passages are in communication upstream of the fuel discharge orifices. The first air and fuel discharge orifices have a relationship to establish a pneumatic pressure at the first fuel discharge orifice and the second air and fuel discharge orifices have a relationship to establish a different pneumatic pressure at the second fuel discharge orifice such that, in the event the supply of fuel to the first and second fuel discharge orifices is interrupted, the fuel residing in the fuel passages between the first and second fuel discharge orifices is subjected to a pressure differential effective to purge the resident fuel into the combustor.

Abstract: Apparatus for cleaning an internal passage of an article, such as a fuel passage of a gas turbine or other engine. The apparatus comprises a container for containing cleaning fluid, means for communicating a first end of the passage to the cleaning fluid in the container, and cleaning fluid conduit means communicated to a second end of the passage in a manner to draw cleaning fluid from the container to flow through the passage from the first end toward the second end in response to flow of cleaning fluid through the conduit means. The apparatus includes means for blocking flow of cleaning fluid through the conduit means so as to direct the cleaning fluid therein to flow through the passage from the second end toward the first end and into the container.

Abstract: Apparatus for cleaning an internal passage of an article, such as a fuel passage of a gas turbine or other engine. The apparatus comprises a container for containing cleaning fluid, means for communicating a first end of the passage to the cleaning fluid in the container, and cleaning fluid conduit means communicated to a second end of the passage in a manner to draw cleaning fluid from the container to flow through the passage from the first end toward the second end in response to flow of cleaning fluid through the conduit means. The apparatus includes means for blocking flow of cleaning fluid through the conduit means so as to direct the cleaning fluid therein to flow through the passage from the second end toward the first end and into the container.

Abstract: A fuel-injector system for a combustor of a gas turbine engine includes first and second fuel injectors rendered operative to discharge fuel to the combustor during a high power regime of engine operation and rendered non-operative during a lower power regime of engine operation. The first and second fuel injectors include respective first and second fuel discharge passages in fuel flow communication to one another and to the combustor via associated fuel discharge lips to sustain a flame region. The first and second fuel injectors are operatively associated with respective first and second air discharge means having air discharge lips for discharging air to the combustor for sustaining the flame region therein.

Abstract: A fuel injector system for a combustor of a gas turbine engine includes first and second fuel injectors rendered operative to discharge fuel to the combustor during a high power regime of engine operation and rendered non-operative during a lower power regime of engine operation. The first and second fuel injectors include respective first and second fuel discharge passages in fuel flow communication to one another and to the combustor via associated fuel discharge lips to sustain a flame region. The first and second fuel injectors are operatively associated with respective first and second air discharge means having air discharge lips for discharging air to the combustor for sustaining the flame region therein. When the fuel injectors are rendered non-operative, different pneumatic pressures are established at the fuel discharge lips to purge fuel from the fuel injectors to the combustor.

Abstract: A fuel injector for a combustor of a gas turbine engine comprises an injector housing having a fuel discharge passage for receiving pressurized fuel and communicated to the combustor for discharging the fuel thereto and an air discharge passage for receiving pressurized air and communicated to the combustor for discharging the air thereto to atomize the discharged fuel. A purge passage in the housing is communicated to the fuel discharge passage at one end and communicated to the air discharge passage at another end. The end of the purge passage is communicated to the air discharge passage by opening directly to the air discharge passage or, alternately, indirectly vis a duct member on the injector housing extending from a region proximate the end of the purge passage to the air passage.

Abstract: The gas turbine combustor air swirler includes a spring temper swirler member having a plurality of air control doors or vanes so cut therein about the longitudinal axis of the combustor inlet as to be integrally and resiliently pivotally connected to the swirler member. The air control doors are progressively canted open to provide predetermined air flow rate and air swirl angle to the combustor inlet in response to increases in air pressure differential thereacross resulting from progressive increases in fuel flow through the nozzle during various regimes of engine operation. The swirler is free of linkages and sliding or other contacting components that are susceptible to binding and other malfunctions in service in the engine.

Abstract: An airblast fuel injector tip is provided for reducing fuel vaporization problems as a result of high fuel temperatures without adversely affecting the airblast operational characteristics of the injector tip. The injector tip includes a fuel receiving chamber and an arcuate valve member movable relative to a valve seat member having a fuel discharge port for discharging fuel flow into the fuel receiving chamber as metered by said valve member in dependence on the pressure of fuel. The valve member comprises an arcuate reed-type valve received in a generally cylindrical tubular valve seat insert with the flow area of the fuel discharge port adjustable externally of the valve seat insert for adjusting the valve cracking pressure.

Abstract: The small airblast fuel nozzle improves cold ignition of small gas turbine engines of the type having a stagnation air pressure of only 1-11/2 inches of water available from the compressor for cold ignition. The fuel nozzle includes an inner air swirling system comprising a longitudinal cylindrical inner air swirl chamber and multiple air inlet slots spaced circumferentially on the nozzle body to supply air to the chamber. The air inlet slots each include an inner tapered section converging toward and into intersection with the chamber and an outer tapered section converging from the exterior of the nozzle body toward and into intersection with the inner section. The inner section and outer section are canted with respect to one another and in the same direction from one slot to the next so that the inner air slots collectively form a hooked cross type pattern when viewed in plan.

Abstract: The small airblast fuel nozzle improves cold ignition of small gas turbine engines of the type having a stagnation air pressure of only 1-11/2 inches of water available from the compressor for cold ignition. The fuel nozzle includes an inner air swirling system comprising a longitudinal cylindrical inner air swirl chamber and multiple air inlet slots spaced circumferentially on the nozzle body to supply air to the chamber. The air inlet slots each include an inner tapered section converging toward and into intersection with the chamber and an outer tapered section converging from the exterior of the nozzle body toward and into intersection with the inner section. The inner section and outer section are canted with respect to one another and in the same direction from one slot to the next so that the inner air slots collectively form a hooked cross type pattern when viewed in plan.

Abstract: An airblast fuel injector tip is provided for reducing fuel vaporization problems as a result of high fuel temperatures without adversely affecting the airblast operational characteristics of the injector tip. The injector tip includes a fuel receiving chamber and a fuel discharge orifice downstream thereof and an arcuate, distensible, tubular valve member having a discharge end movable relative to a valve seat in the fuel receiving chamber in dependence on the pressure of fuel in the valve member to meter fuel to the fuel receiving chamber for discharge through the discharge orifice into a combustor.

Abstract: The small airblast fuel nozzle improves cold ignition of small gas turbine engines of the type having a stagnation air pressure of only 1-1-1/2 inches of water available from the compressor for cold ignition. The fuel nozzle includes an inner air swirling system comprising a longitudinal cylindrical inner air swirl chamber and multiple air inlet slots spaced circumferentially on the nozzle body to supply air to the chamber. The air inlet slots each include an inner tapered section converging toward and into intersection with the chamber and an outer tapered section converging from the exterior of the nozzle body toward and into intersection with the inner section. The inner section and outer section are canted with respect to one another and in the same direction from one slot to the next so that the inner air slots collectively form a hooked cross type pattern when viewed in plan.

Abstract: An airblast fuel injector tip is provided for reducing fuel vaporization problems as a result of high fuel temperatures without adversely affecting the airblast operational characteristics of the injector tip. The injector tip includes a fuel receiving chamber and an arcuate valve member movable relative to a valve seat member having a fuel discharged port for discharging fuel flow into the fuel receiving chamber as metered by said valve member in dependence on the pressure of fuel. The valve member comprises an arcuate reed-type valve received in a generally cylindrical tubular valve seat insert with the flow area of the fuel discharge port adjustable externally of the valve seat insert for adjusting the valve cracking pressure.

Abstract: An airblast fuel injector tip is provided for reducing fuel vaporization problems as a result of high fuel temperatures without adversely affecting the airblast operational characterisitics of the injector tip. The injector tip includes a fuel receiving chamber and an arcuate valve member movable relative to a valve seat member having a fuel discharge port for discharging fuel flow into the fuel receiving chamber as metered by the valve member in dependence on the pressure of fuel. The valve seat member is adjustably received on the injector tip and preferably includes a deflectable portion accessible externally of the injector tip for facilitating adjustment of the valve cracking pressure.

Abstract: An airblast fuel injector tip is provided for reducing fuel vaporization problems as a result of high fuel temperatures without adversely affecting the airblast operational characteristics of the injector tip. The injector tip includes a fuel receiving chamber and a fuel discharge orifice downstream thereof and an arcuate, distensible, tubular valve member having a discharge end movable relative to a valve seat in the fuel receiving chamber in dependence on the pressure of fuel in the valve member to meter fuel to the fuel receiving chamber for discharge through the discharge orifice into a combustor.

Abstract: A modular fuel nozzle assembly includes a precalibrated, stand-alone valve module having a fuel metering valve and a precalibrated, stand-alone nozzle module having a fuel injection nozzle. The valve module and nozzle module include separate support housings joined together at an interface between the two modules to facilitate manufacturing, testing and maintainability of the fuel nozzle assembly. Fuel tubes extend across the interface to interconnect fuel passages in the joined modules.