Abstract: A fuel pumping and transfer system for a multiple concentric shaft gas turbine engine which has the capability to handle contaminated or slurry fuels. The fuel is introduced into the innermost shaft at any desired low pressure thereby eliminating the need for a high pressure fuel pump. Fuel is introduced through a rotating fuel tube disposed within the inner shaft of the engine. The centrifugal force caused by rotation of the shafts causes the fuel to be collected against the inner wall of the shaft creating a centrifugal pressure dam. As the fuel passes from one collection region to the next the differential pressure between the inner shaft region and the combustor increases sufficiently to provide proper combustion.

Abstract: A low cost, integrated, aircraft fuel management system. A system control unit receives engine variable signals and provides a signal to a motor control unit which thereby controls a variable speed motor. The motor drives a positive displacement pump which delivers and meters fuel to a slinger type turbine engine capable of handling slurry fuels. In a preferred embodiment, compressor discharge pressure (CDP) is supplied to the airframe fuel reservoir thereby pressurizing the fuel supply and minimizing the power requirements of the motor driving the fuel pump.

Abstract: The present disclosure provides an inexpensive self contained lubrication system for the bearing which rotatably mounts a turbine engine shaft to the support housing in a turbine engine. The lubrication system includes a first seal assembly which extends between the shaft and the housing at a position axially spaced from one side of the bearing assembly and a second seal assembly extending between the shaft and the housing at the position axially spaced from the other side of the bearing assembly. The bearing assemblies form a sump chamber in the support housing which contains a lubricant. Each bearing assembly includes a resilient O-ring extending between the shaft and the support housing while two impellers attached to the shaft within the sump chamber pump the lubricant in the sump chamber through the bearing assembly and back to the sump chamber during shaft rotation.

Abstract: A low cost, integrated, aircraft fuel management system. A system control unit receives engine variable signals and provides a signal to a motor control unit which thereby controls a variable speed motor. The motor drives a positive displacement pump which delivers and meters fuel to a slinger type turbine engine capable of handling slurry fuels. In a preferred embodiment, compressor discharge pressure (CDP) is supplied to the airframe fuel reservoir thereby pressurizing the fuel supply and minimizing the power requirements of the motor driving the fuel pump.

Abstract: A unique fuel system for supplying fuel from a fuel source and to a turbine engine is disclosed and comprises a fuel inlet conduit having one end adapted for connection with the fuel source and a fuel outlet conduit having one end adapted for connection with the turbine engine. The other end of the inlet and outlet conduits are connected to a valve movable between a bypass and operating condition. Both ends of a third conduit are also connected to the valve while a fuel pump is fluidly connected in series with and at a midpoint of a third conduit. In its bypass position, the valve fluidly connects the inlet and outlet conduits together while simultaneously sealingly closing the third conduit and entrapping any fuel contained therein. In its operating condition, the valve simultaneously connects the inlet conduits with one end of the third conduit and the other end of the third conduit to the outlet conduits thus supplying fuel to the engine.

Abstract: A turbine engine construction comprising a support housing, a compressor, combustor and turbine expander contained within the support housing. The combustor includes a combustor housing defining an inner combustion chamber and an outer chamber between the combustor housing and the support housing. Compressed air from the compressor outlet is communicated to the combustion chamber into which fuel is injected and ignited so that the resulting combustion products expand through a turbine nozzle and into the turbine expander. The novelty of the present invention resides in the construction of a diffuser assembly integrated with both the turbine nozzle and combustor. The diffuser assembly comprises a plurality of diffuser tubes, each tube having one end open to and in registration with the compressed air outlet of the compressor. The other ends of the tubes are arranged in at least two discharge planes for the combustor to improve and increase induced mixing and swirl in the combustion chamber.

Abstract: A turbine engine construction of the type having a support housing, a compressor and at least one turbine stage rotatably mounted in the support housing, said turbine stage having an annular rotating shroud secured around its outer periphery while a static shroud is connected to the support housing coaxially around and spaced radially outwardly from the rotating shroud thus defining a clearance space between the two shrouds. The novelty of the invention resides in a system for cooling both the static and rotating shrouds and for also simultaneously substantially reducing or eliminating the leakage of hot gases through the clearance space between the shrouds. In the preferred form of the invention, this system comprises a plurality of circumferentially spaced ports formed through the housing and/or static shroud. Each port has one end open to the compressed air outlet from the compressor and its other end open to the clearance space between the shrouds.

Abstract: In a turbine engine of the type having a centrifugal air compressor open at one end to a combustion chamber, the improvement which comprises coating the back face of the air compressor with a thermal insulating material, such as zirconium oxide. The thermal insulating material effectively insulates the relatively cool air compressor from hot leakage gases from the combustor and subsequent turbine engine components thus minimizing thermal strain on the compressor and enabling higher compressor speeds and pressure ratios and/or reduced compressor weight.

Abstract: A rotating slinger fuel injector for turbine engines is provided with a plurality of radial holes for distributing and mixing fuel and air throughout the combustor. Fuel is supplied from a stationary fuel manifold through fuel ports in a rotating slinger which distributes the fuel in a plurality of planes throughout the combustor. Air is channeled from the compressor rotor through radially and axially angled air ports provided in the slinger so as to distribute air in a plurality of planes which intersect the planes of distributed fuel at various points throughout the interior combustor. Thus the combustion intensity and efficiency is greatly increased.

Abstract: An improved transpiration cooled turbine blade has a porous wall for the passage of coolant fluid therethrough; the wall comprising an outer porous layer, a second layer with relatively large holes, and a third layer with metering holes for the cooling fluid. There is provision for the direct passage of coolant to the edges of the blade, which edges are single layered. Slots near the trailing edge of the blade direct a portion of the cooling fluid outwardly at a right angle to the blade's concave surface to reduce drag losses due to flow separation under conditions of high blade loading.