Abstract: A small aero gas turbine engine with an axial thrust limiter device that uses compressed air acting on a rotating disk extending from a rotor of the engine in which a forward pressure chamber and an aft pressure chamber applies a pressure to both sides of the rotating disk. When rotor is shifted, one side of the rotating disk has an increase in pressure acting on it to shift the rotor in an axial direction. Each pressure chamber includes an upper variable restriction and a lower variable restriction in which the restriction varies due to axial movement of the rotor. A forward and an aft foil bearing can also be used in addition to axial balance the rotor when not enough pressure is available such as at engine startup.

Abstract: A heat reservoir for use in a power plant that burns a dirty fuel such as coal to absorb the heat from the resulting dirty hot gas flow. The heat reservoir includes a number of heat absorbing walls that form dirty hot gas flow passages and clean hot gas flow passages. Cross-over holes are formed in the walls to equalize pressure. The dirty hot gas flow is passed though the dirty passages to heat up the walls. When the heat absorbing walls have absorbed enough heat, the dirty hot gas flow is stopped and compressed air is passed through the clean passages to absorb heat from the walls and is then passed through a turbine to drive an electric generator. The heat reservoir is then recharged again by passing the dirty hot gas flow through the dirty passages to recharge the walls.

Abstract: A electrical power plant with a gas turbine engine that drives two electric high speed generators connected on the two ends of the engine rotor shaft in a direct drive relation without the need for a gear box. The high speed generators can be of the same or different power rating and connected in series such that the total power output can easily be changed without the need to redesign larger high speed generators. Because the generators use permanent magnets, they can be operated as motors to drive two or more compressors. A turbine can be used to drive two or more high speed generators connected in series. Since the high speed generator/motors have thrust bearings, the thrust bearing in the turbomachine can be eliminated.

Abstract: A power plant with an industrial gas turbine engine or a steam turbine to drives an electric generator to generate electric power. The compressor of the IGT or the condenser of the steam turbine is connected to a heat exchanger to cool the compressor inlet air or the steam passing through the condenser. The heat exchanger is located in or near an open source of water that has naturally cold water at a certain depth, and cold water is pumped from the open source and through the heat exchanger to pre-cool the air. The pre-cooled air passing through the heat exchanger will cool the compressor inlet air or cool the steam in the condenser to increase the efficiency of the IGT or steam turbine.

Abstract: A transition duct used in a gas turbine engine to direct the hot gas flow from the combustor into the turbine section of the gas turbine engine. The transition duct includes a plurality of guide vane integral with the duct. The transition duct includes a circular shaped inlet end for connection to a can combustor and a rectangular and arched shaped outlet end for connection to a first stage turbine section. the guide vanes extend within the flow path between inner and outer projections each having a curved opening in the shape of the airfoil each airfoil includes inner and outer airfoil ends with retainer slots formed between the airfoil ends and the duct projections that form shear pin retainer slots. Shear pin retainers are secured within the slots to secure the guide vanes to the duct in a thermally uncoupled manner to reduce thermal stresses. The guide vanes can be made from a single crystal material for higher gas flow temperatures.

Abstract: A gas turbine engine with a rotor shaft that is moveable in an axial direction so change a blade tip clearance, where the rotor is displaced by a spring to increase the blade tip clearance and is displaced by a pressure created by the compressor and turbine during engine operation that will close the blade tip clearance. This is especially useful during engine shutdown to prevent blade tip rubbing against the stationary shrouds.

Abstract: A power plant for burning a fuel in a low pressure combustion chamber to produce electrical power. A first compressor supplies compressed air through a first heat exchanger to add heat to the compressed air. The heated compressed air is passed through a first turbine to drive a first electric generator. The first turbine outlet is passed through a second heat exchanger in series with the first heat exchanger to further heat the compressed air. The compressed air is then passed through a second turbine to drive a second electric generator and produce electric power. The outlet from the second turbine is passed through a first combustor to produce the hot gas flow through the second heat exchanger. The outlet from the second heat exchanger is passed through a second combustor before passing through the first heat exchanger. The outlet from the first heat exchanger is passed through a heat recovery steam generator to generate steam to drive another turbine and another generator.

Abstract: A power plant that is used for storing energy during a low demand and returning the energy to a power plant during high or peak demand. A concrete tank is placed on the bottom of a deep body of water. A compressed air line connects the tank to a compressor and turbine assembly on land at the power plant. An electric motor drives the compressor to supply compressed air to the tank and displace the water within the tank during the low demand period. At high demand, the compressed air is allowed to flow through the turbine that drives an electric generator to produce electric power. The tank includes a water outlet pipe for the tank is displaced of the high pressure water and to allow the water to flow into the tank and displace the compressed air under high pressure to drive the turbine.

Abstract: A gas turbine engine with a turbine section having at least a first stage turbine blade and a last stage turbine blade. The first stage turbine blade includes cooling fluid passages therein in which a compressed cooling fluid, usually from the compressor section of the gas turbine engine, is passed through for cooling of the first stage blade. The last stage turbine blade includes cooling fluid passages therein, but draws the cooling air from an outside ambient pressure source instead of from a compressor. The rotation of the last stage turbine blade and rotor disk provides for a centrifugal force to drive the cooling air into the blade and through the blade for cooling thereof. No additional compression of the last stage cooling fluid is required. A cover plate with a plurality of impellers covers a back side of the last stage rotor disk and provides for an additional means to pump the ambient cooling fluid into the last stage blade.

Abstract: A test rig that reproduces high temperature and high pressure conditions found in a gas turbine engine for testing materials under these conditions. The test rig is formed of a plurality of modules connected in series to form the test rig. A specimen rotation module is connected to a mechanical load module, which is connected to a combustor module, which is connected to a test section module on which one or more test specimens are placed, which connects to an exhaust section module, which is connected to a thrust bearing & air inlet section module. The modules are cylindrical in shape and connected in series to form a compact test rig.

Abstract: A turbine airfoil with a plurality of breakout passages located just beneath a thermal barrier coating or just beneath the metal surface of the airfoil. The breakout passages are connected to an internal cooling air passage and allow for film cooling air to flow when a surface over the breakout passage has been chipped or eroded away to provide for additional cooling to the damaged airfoil surface. The breakout passages are formed during the casting process of the airfoil using a plurality of molding pieces. The breakout passages are formed along a direction of the pulling direction of the respective mold piece. This allows for the solidified airfoil to be easily removed from the mold assembly.

Abstract: A power plant that burns a dirty fuel like coal to produce a hot gas stream, and directs the hot gas stream into a turbine to produce power. Located between the combustor and the turbine is at least two heat reservoirs that operate in parallel. When a first heat reservoir is being supplied with hot gas stream from the combustor to collect heat therein, the second and parallel heat reservoir is discharging its stored heat into a hot gas stream that leads into the turbine to produce power. When the heat reservoir delivering the hot gas stream to the turbine is low, the gas flow paths are switched such that the heat reservoir with the low heat storage in charged while the near fully charged heat reservoir then delivers heat to drive the turbine.

Abstract: A floating wind turbine in which a floating barge having a doughnut shape with an open center rigidly supports a plurality of airfoils such that a wind produces a rotation of the blades and the barge. The airfoil and barge assembly is connected to a rigid shaft that extends into a generator housing that houses a generator. Anti-rotation fins extend from the generator housing and into the water to limit rotation of the generator housing as the blades and barge rotates in the wind. Rotation of the rigid shaft due to the wind also rotates the generator shaft to produce electricity. The floating turbine supports the blades for rotation without the need for bearings so the turbine can be extremely large. The blades are supported by the floating barge so the blades can also be extremely large. The barge is doughnut shaped to limit viscous forces due to rotation of the barge within the water. A second floating wind turbine rotates within the first floating turbine but in an opposite direction.

Abstract: A test facility is provided for testing materials under high temperature, pressure, and mechanical loads. The facility provides a physically scaled system that simulates conditions in hot sections of gas turbine engines. A test article is coated with a test material and exposed to a hot combusting flow in a test section housing. The article may be a pipe or conduit member oriented at any direction to the flow. A second cooler flow of fluid is channeled through the test article to create a sharp temperature gradient in the test article and through the test material. A liquid-cooled sleeve is disposed about the test article to create an annular channel of combusting flow over the test article. The downstream end of the second cooler flow is connected to the upstream end of the main hot flow at the combustion chamber.

Abstract: A test facility is provided for testing materials under high temperature, pressure, and mechanical loads. The facility provides a physically scaled system that simulates conditions in hot sections of gas turbine engines. A test article is coated with a test material and exposed to a hot combusting flow in a test section housing. The article may be a pipe or conduit member oriented at any direction to the flow. A second cooler flow of fluid is channeled through the test article to create a sharp temperature gradient in the test article and through the test material. A liquid-cooled sleeve is disposed about the test article to create an annular channel of combusting flow over the test article. The downstream end of the second cooler flow is connected to the upstream end of the main hot flow at the combustion chamber.

Abstract: A power plant that includes two combustors in which a particulate containing fuel like coal is burned in one combustor and a non-particulate or clean fuel is burned in the other combustor, and where a heat exchanger is sued to transfer heat from the particulate combustion process to compressed air stream leading into the non-particulate combustor. The outlet from the heat exchanger containing the particulate combustion product is delivered to a heat recovery steam generator to produce steam and drive a turbine. The non-particulate combustion product from is used to drive a second turbine, and the outlet from the turbine is delivered to the inlet of the particulate combustor to be mixed with a particulate containing fuel. The invention allows for the use of a relatively cheap fuel such as coal to be used in a gas turbine power producing plant.

Abstract: A test facility is provided for testing materials under high temperature, pressure, and mechanical loads. The facility provides a physically scaled system that simulates conditions in hot sections of gas turbine engines. A test article is coated with a test material and exposed to a hot combusting flow in a test section housing. The article may be a pipe or conduit member oriented at any direction to the flow. A second cooler flow of fluid is channeled through the test article to create a sharp temperature gradient in the test article and through the test material. A liquid-cooled sleeve is disposed about the test article to create an annular channel of combusting flow over the test article. The downstream end of the second cooler flow is connected to the upstream end of the main hot flow at the combustion chamber.

Abstract: In a method of operating a multi-stage combustion chamber, having at least one primary burner (110) of the premixing type of construction, the fuel injected via nozzles is intensively mixed with primary combustion air inside a premixing space in advance of the ignition. Secondary combustion air is directed into a secondary combustion space (62) which is arranged downstream of the precombustion space (61). The primary burner (110) is a flame-stabilizing double-cone burner without a mechanical flame retention baffle, which is operated at the lower stability limit. The burnt gas is accelerated between precombustion space (61) and secondary combustion space (62). For the purpose of forming a self-igniting mixture, cooling air from the double-wall combustion-chamber boundary and additional fuel are introduced into the burnt-gas flow leaving the precombustion space.