Abstract: A first stage gas nozzle for directing a combustion gas stream onto the rotatable blades of a gas turbine contains a plurality of spaced air-foil shaped vanes, each vane containing a steam nozzle to direct steam as a thermal barrier over the exterior surfaces of the vane. A steam nozzle in the trailing edge of each vane directs heated coolant steam from the interior of the vane to the gas streams. Disruption of the laminar steam film in the trailing edge steam nozzle such as by the provocation of a shock wave or by diffusion separation exposes the bare surfaces of the trailing edge steam nozzle to the coolant steam thereby improving heat transfer at the extreme trailing edge of the vane.

Abstract: A reheat gas and double reheat steam turbine combined cycle is provided in which the outer compressor shell and gas generator turbine are modified for steam cooling to control tip clearances of the rotating blades of the compressor and gas generator turbine with the respective shells which confine the blading.

Abstract: In order to operate a gas turbine and steam turbine plant with a high temperature at the inlet to the gas turbine plant, the parts located in the hot-gas stream of the gas turbine being steam-cooled, and the cooling steam, thereby raised to a higher temperature, being fed to the steam turbine for further expansion, it is proposed that the waste heat from the gas turbine (3) be led through a two-pressure waste heat boiler (7), and that the steam, generated in this boiler, be slightly superheated in a cooling-steam superheater (10), and fed to the hollow inlet vanes (43) and to the rotor blades (42), which are likewise hollow, the steam, strongly superheated during this cooling process, then being admixed to the steam coming from the intermediate superheater (13), and being fed to the low-pressure section of the steam turbine (27).

Abstract: Part of high-pressure air is extracted from the vicinity of the final stage of a compressor and is introduced into a water spraying chamber, and water at the normal temperature is injected into the high-pressure air from a nozzle installed in the water spraying chamber, to prepare a cooled coolant. The coolant sometimes contains water drops. The cooled coolant is fed into coolant passageways which are provided inside a moving blade in a manner to extend from the root part to the tip of the moving blade. When the coolant passes through the passageways, the moving blade is cooled by the coolant, and after the cooling, the coolant is emitted into a turbine main gas passageway. In case where the water drops are contained in the coolant, they vaporize during the cooling of the moving blade, to cool the air of the coolant, to suppress the temperature rise of the coolant and to enhance the cooling effect.

Abstract: A gas turbine engine is disclosed which has an integral steam power system consisting of heat absorbing boilers which convert an unpressurized liquid into an expanded and heated steam by utilizing heat normally lost through component cooling systems and the exhaust system. Upon completion of the steam power cycle, the steam is condensed back to a liquid state through a condensing system located within the compressor and other functional components of the gas turbine engine. A system of high pressure air and friction seals restrict steam or liquid condensate within designed flow bounds. The gas turbine engine disclosed is designed to give improved fuel efficiency and economy for aircraft and land use applications.

Abstract: Steam-cooling with a steam thermal barrier for reheat gas turbine vanes and blades offers advantages over cooling with air or water at the higher temperatures characteristic of existing high temperature gas tubines, in particular when coupled with a reheat steam cycle. Consequently, in such a combined cycle, higher cycle efficiency is obtainable for gas turbine initial firing temperatures of about 2500.degree. F. (1371.degree. C.) and 2050.degree. F. (1121.degree. C.) reheat temperatures where over-all combined cycle degradation resulting from steam cooling is below about 1%. A proposed combined reheat gas turbine and steam turbine cycle includes a gas turbine having steam-cooled components operating at a cycle pressure ratio of about 38 without intercooling and includes steam superheating in the reheat combustor.

Abstract: The disclosure illustrates a sealing assembly for two relatively rotatable members, such as a compressor housing and a shaft for a compressor wheel. The first has an internal cylindrical surface and the second has an external cylindrical surface with an annular groove therein. The second member is disposed and rotatable within the first member and a sealing ring is disposed in the annular groove. The sealing ring is a continuous member having no circumferential gaps and made from PTFE which has sufficient elasticity to enable the radially inner diameter of the ring to be temporarily increased. It is also capable of working at the temperatures to which the assembly is subjected in use and has a low coefficient of friction.

Abstract: A bearing mounting with cooling means is provided which is particularly suited for use in turbine engines. The device comprises a housing coaxially connected to a rotating shaft while a bearing is operatively disposed between a relatively stationary member and one end of the housing. A heat sink, which can comprise one or more stages of compressor for the turbine engine, is connected to the other end of the housing. An annular fluid chamber is formed axially along the housing between its ends and tapers radially outwardly from the second end and to the first end of the housing. The annular chamber is partially filled with a heat conductive liquid. Heat energy from the bearing is conducted to the liquid which vaporizes and expands toward the second end of the housing whereupon the heated gas transfers its heat energy to the heat sink and recondenses. The recondensed liquid is then returned by centrifugal force to the first end of the housing.

Abstract: A liquid cooled stator blade assembly for a gas turbine engine includes an outer shroud having a pair of liquid inlets and a pair of liquid outlets supplied through a header and wherein means including tubes support the header radially outwardly of the shroud and also couple the header with the pair of liquid inlets and outlets.

Abstract: An aerofoil blade for a gas turbine engine is in the form of a heat pipe. The aerofoil blade has an internal passageway adapted to contain a secondary structure and to thermally insulate that secondary structure from the remainder of the aerofoil blade by, for instance, the provision of a cooling air passage between the internal passageway and secondary structure.

Abstract: A turbine for a gas turbine engine is provided with a rotary stage comprising an annular array of rotor blades surrounded by an annular shroud member. The shroud member is hollow, the hollow interior being provided with a heat transfer medium which, in operation, functions as a condensable vapor and liquid whereby the shroud member is a heat pipe. The shroud member is further provided with a wall adjacent the aerofoil blade which is adapted to be penetrable by a detached blade or blade portion. The wall of the shroud member is dimensioned so that any such detached blade or blade portion which penetrates the wall enters the hollow shroud ring and is retained within it.

Abstract: The turbine blades of a gas turbine engine are individually cooled through the internal circulation of a fluid coolant by the thermosiphon principle. Each turbine blade has associated therewith a closed-loop coolant passageway which is rotatable with the turbine rotor disk and which, in one embodiment, passes through a heat exchanger borne by, and rotatable with, a rotatable lubrication duct. The blade internal coolant is placed in heat exchange relationship with engine lubrication oil within the heat exchanger. The heated lubrication oil is then placed in heat exchange relationship with the engine fuel and the fuel thus heated is burned in the combustor, thereby returning at least a portion of the heat removed from the turbine blades to the engine power cycle. The cooling system is designed for simplified blade removal and replacement and the entire turbine can be removed from the engine as a sealed unit.

Abstract: A water-cooled turbine rotor blade having an enlarged radially-extending chamber forming a coolant reservoir connected to cooling passages subadjacent the blade surface. The channels interconnecting the reservoir with the passages are adjacent the blade tip so that the pressurized water (i.e., due to the centrifugal force caused by the rotation) in the reservoir flows into the channels at the tip and thence through the cooling passages radially inwardly. Heat absorption from the blade causes vaporization of the water as it flows through the passages. The cooling passages terminate radially inwardly (adjacent the hub or root portion) in a space in flow communication with the enlarged chamber and an exhaust port in the downstream face of the root so that vapor is exhausted at the downstream face and any liquid exiting the coolant passages is returned to the reservoir.

Abstract: The blades of a gas turbine are primarily cooled by the circulation of a coolant through the hollow interiors thereof by the thermosiphon principle. Each hollow blade interior is also placed in fluid communication with a secondary coolant source, but secondary coolant flow is precluded by a plug filling the inlet fluid passage. Similar plugs fill apertures in the form of casting holes through each blade airfoil portion, the holes serving to discharge the secondary coolant from the blade interior. The plugs are fabricated of a material having a lower melting point temperature than that of the remainder of the blade airfoil portion such that, in the event of failure in the primary cooling system, the plugs will melt, thereby permitting the secondary coolant to rush through the blade and provide internal cooling thereof.

Abstract: A method and apparatus for generating heat and vaporizing of liquids, and for providing cooling by using a continuous flow centrifuge to compress a gas with accompanying temperature increase and removing heat to another fluid from said gas in compressed state; said gas then being passed from the first rotor via nozzles mounted on said first rotor in backward direction thus reducing the absolute tangential velocity of said gaseous fluid; said gaseous fluid being then passed to a second rotor for which the rotor tip speed may be nearly the same as the velocity of said entering gaseous fluid. After said gaseous fluid enters the second rotor, it is then passed inward within said second rotor and discharged near said second rotor center. Work is supplied to said first rotor normally, and recovered in said second rotor. The gaseous fluid may be air, carbon dioxide, or some other fluid. The fluid receiving said heat may be water, ammonia, or some other fluid.