Abstract: A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes a pair of legs extending radially outwardly from an outer shroud and a pair of mounting legs extending radially inwardly from an inner shroud. Each of the pair of legs and mounting legs have a pair of holes therein. A plurality of members attached to the gas turbine engine have a plurality of bores therein which axially align with corresponding ones of the pair of holes in the legs. A plurality of pins are positioned within the corresponding holes and bores radially positioning the nozzle guide vane assembly about a central axis of the gas turbine engine.

Abstract: The control systems for reducing NOx in the combustion systems of past gas turbine engines has incorporated a variety of expensive and complicated techniques to reduce the NOx level. For example, such systems use schemes for introducing more air into the primary combustion zone, recirculating cooled exhaust products into the combustion zone and injecting water spray into the combustion zone. The present system (12) reduces the formation of NOx within the combustion zone by controlling the air/fuel ratio and more explicitly by controlling the air portion of the air/fuel ratio. The present system (12) includes a device (260) for directing a portion of the flow of compressed air exiting a compressor section (22) into an injection nozzle (60,180,330) and into a combustor (40), and further includes a device (298) for reducing the flow of compressed air into the combustor (40).

Abstract: Electric machines are used to produce electrical energy or are driven by electrical energy. Such machines include a stator assembly and a rotor assembly rotationally positioned within the stator assembly. A gap is formed between the rotating element and the stationary element. To increase the life and efficiency of many electric machines, heat formed within the gap is carried away by passing a cooling media through the gap. The present electric machine includes a cooling system wherein the electric machine is positioned in an inlet plenum of a gas turbine engine. Compressed air from the gas turbine engine is used to cool the gap of the electric machine. An expansion turbine is attached to the rotor assembly upstream of the gap and has high pressure gap cooling air directed through the expansion turbine into the gap to cool the electric machine.

Abstract: An axial flow turbine's nozzle/nozzle support structure having a cantilevered nozzle outer structure including an outer shroud and airfoil vanes extending radially inwardly therefrom, an inner shroud radially adjacent the inner end of the airfoil vanes and cooperatively disposed relative to the outer shroud to provide an annular fluid flow path, an inner and an outer support ring respectively arranged radially inside the inner shroud and axially adjacent a portion of the outer shroud, and pins extending through such portion and into the outer support ring. The inner support ring or inner shroud has a groove therein bounded by end walls for receiving and being axially abuttable with a locating projection from the adjacent airfoil vane, inner shroud, or inner support ring.

Abstract: A turbine blade having a preestablished rate of thermal expansion is attached to a turbine disc having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade and forms a turbine assembly. The turbine blade has a root portion defining a pair of sides having a pair of grooves therein. The turbine assembly includes a pair of flanges between which the turbine blades are positioned. Each of the pair of flanges has a plurality of grooves defined therein. The grooves within the pair of flanges are aligned with the grooves in the blades and have a space formed therebetween. A plurality of spherical balls are positioned within the space. The plurality of spherical balls has a preestablished rate of thermal expansion being equal to the preestablished rate of thermal expansion of the turbine blade.

Abstract: Past fuel injection nozzles have attempted to provide a structure to reduce exhaust emissions, generally NOx using water injection. Such nozzles have failed to attain adequate reduction of exhaust emissions. The present fuel injector structure has resulted in reduced NOx emissions. The structure includes a combustor having an axis a first air flow passage, a second air flow passage, a first annular fuel passage and a second annular fuel passage. Positioned in the first air flow passage is a directing device through which water is introduced in a swirling manner and mixed with the air in the first air flow passage. Fuel is introduced into the first and/or second annular fuel passages and mixed with air in the second air flow passage. The mixtures of air and water, and fuel and air are mixed prior to entering the combustion section. The unique structure swirls the air and fuel and the air and water prior to their meeting and mixing.

Abstract: A turbine blade having a preestablished rate of thermal expansion is attached to a turbine wheel having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade. The turbine wheel includes a pair of side walls having a groove formed therebetween and a pair of axially aligned holes radially positioned therein. The turbine blade has a root portion having a bore positioned therein. A pin having a preestablished rate of thermal expansion being substantially equal to the rate of thermal expansion of the blade is positioned within the axially aligned holes and the bore attaches the blade to the turbine wheel.

Abstract: Fuel injection nozzles used for reducing NOx in gas turbine engines have incorporated a variety of expensive and complicated techniques. For example, systems use schemes for introducing more air into the primary combustion zone, recirculating cooled exhaust products into the combustion zone and injecting water spray into the combustion zone. The present dual fuel injector reduces the formation of carbon monoxide, unburned hydrocarbons and nitrogen oxides within the combustion zone by providing a series of premixing chambers being in serially aligned relationship one to another. During operation of the dual fuel injector the premixing chambers have a liquid fluid and air or water and air being further mixed with additional air or a gaseous fluid and air. The liquid fluid and the gaseous fluid can be use simultaneously or individually depending on the availability of fluids.

Abstract: Past systems have attempted to cool the combustor end or tip of fuel injection nozzles by dumping the spent cooling air directly into combustion zone where it can adversely affect the combustion process in general, and NOx and CO emissions in particular. The present system or structure for cooling a combustor end or tip uses a circulating device which in this application is an annular groove positioned in the tip through which fuel is circulated and absorbs heat directly from the tip and indirectly from the combusting gases being produced in the combustion zone. After cooling the tip the fuel exits into a mixing chamber. The mixture of fuel and combustion air is then introduced into the combustion zone, thus, avoiding the direct injection of fuel into the combustion zone. The fuel enters an inlet opening and exits an outlet opening which are positioned about 180 degrees one from the other.

Abstract: A turbine blade having a preestablished rate of thermal expansion is attached to a turbine wheel having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade. The turbine blade has a root portion having a first groove and a second groove therein. The turbine wheel includes a plurality of openings in which the turbine blade is positioned. Each of the openings has a first groove and a second groove therein. The space or void formed between the first grooves and the second grooves has a plurality of spherical balls positioned therein. The plurality of spherical balls has a preestablished rate of thermal expansion being equal to the preestablished rate of thermal expansion of the turbine blade.

Abstract: A nozzle guide vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The nozzle guide vane assembly includes an outer shroud having a mounting leg with an opening defined therein, a tip shoe ring having a mounting member with an opening defined therein, a nozzle support ring having a plurality of holes therein and a pin positioned in the corresponding opening in the outer shroud, opening in the tip shoe ring and the hole in the nozzle support ring. A rolling joint is provided between metallic components of the gas turbine engine and the nozzle guide vane assembly. The nozzle guide vane assembly is positioned radially about a central axis of the gas turbine engine and axially aligned with a combustor of the gas turbine engine.

Abstract: A turbine blade having a preestablished rate of thermal expansion is attached to a turbine wheel having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade. The turbine blade has a root portion having a pair of recessed portions thereon. The turbine wheel includes a plurality of openings in which the turbine blade is positioned. Each of the openings have a pair of grooves therein in which are positioned a pair of pins having a generally rectangular cross-section and a reaction surface thereon. A pair of cylindrical rollers interposed respective ones of the pair of reaction surfaces and the pair of recessed portions. The attachment system or turbine assembly provides an economical, reliable and effective attachment of a component having a preestablished rate of thermal expansion to a component having a greater preestablished rate of thermal expansion.

Abstract: Past systems have attempted to provide a combustion system to reduce NOx pollution, however, such methods have failed to attain adequate reductions in NOx pollution. The present system or structure for for reducing NOx includes a pilot fuel system and a premixed supply system to reduce the NOx to a workable level. The pilot system uses a device for supplying combustible fuel to the fuel injection nozzle generally along a combustion axis during all or a portion of the operating conditions of the engine. Low NOx is maintained by using a device for supplying combustible fuel into each of a plurality of spaces formed between a plurality of swirler vanes. Low NOx is further maintained by having the cooling fluid used to cool the fuel injection nozzle mixed with the fuel and air from the spaces prior to entering the combustion chamber.

Abstract: Fuel injection nozzles used for reducing NOx in gas turbine engines has incorporated a variety of expensive and complicated techniques. For example, systems use schemes for introducing more air into the primary combustion zone, recirculating cooled exhaust products into the combustion zone and injecting water spray into the combustion zone. The present fuel injector (60,166) reduces the formation of carbon monoxide, unburned hydrocarbons and nitrogen oxides within the combustion zone by controlling the premix air/fuel ratio and more explicitly by controlling the air portion of the air/fuel ratio over the entire operating range of the engine (10).

Abstract: The lean premix combustion approach for NOx emissions control in gas turbine combustion systems has led to the problems of increased combustion pressure oscillation during engine operation and flame outs during rapid engine load reduction. Combustion pressure oscillation can reduce the durability of the engine and combustion system components to unacceptable levels. Flame outs can make the engine unacceptable from the operational viewpoint. The use of a control device allows the combustion pressure oscillation amplitude to be controlled to levels required for long durability of the combustion system components. It also allows an engine control system to operate the engine at part load condition and during rapid load reduction without flame out. When used at small levels, its effect on the engine NOx emissions is small. Higher levels may sometimes be needed to control the combustion pressure oscillation to acceptable levels.

Abstract: A head gasket assembly (18) is used for sealing a joint between a cylinder block (12) and a cylinder head (14). At least portions of the head gasket assembly (18) must withstand high temperatures, high pressures and be flexible for sealing fluid passages such as lubricating oil and cooling water mixtures. The present head gasket assembly (18) is comprised of a main gasket body (40) constructed of a sealing material (46) having a plurality of apertures (48,50,52) positioned therein. A portion of the plurality of apertures (48,50,52) includes a combustion opening (52) having a first ring (54) positioned in the periphery of the combustion opening (52). A plurality of tape strips (60) having an end portion (62) attached to a side of the sealing material (46), partially surrounding the fire ring (54) and another end portion (64) attached to the other side of the sealing material (46).

Abstract: The known control systems for reducing NOx in the combustion systems of past gas turbine engines has incorporated a variety of expensive and complicated techniques to reduce the NOx level. The present apparatus reduces the formation of NOx within the combustion zone by controlling the air portion of the air/fuel ratio. The present apparatus includes a device for controllably varying the quantity of compressed air directed into a manifold resulting in controlling the air to a plurality of injection nozzles and into a combustor. A throttling mechanism moves between an open position and a closed position varying the flow rate of compressor air to the combustor apparatus provides an economical, reliable and effective method for reducing and controlling the amount of nitrogen oxide (NOx) carbon monoxide (CO) and unburned hydrocarbon (UHC) emitted from the gas turbine engine.

Abstract: The design and construction of past piston assemblies having a wrist pin bolted to a connecting rod have excessive weight and structural components, and requires more complex machining techniques and tooling. The present invention overcomes these problem by providing a piston assembly (30) with a wrist pin (36) attached to a piston member (32). Thus, the length of the leg members (80) are short and do not require a portion surrounding the wrist pin (36). The results being reduced piston member (32) and piston assembly (30) weight and lower inertia, a simplified forging or casting process, a more easily machinable cavity (86) within the piston member (32) and a higher quality piston assembly (30).

Abstract: Past fuel injection nozzles have attempted to provide a structure to reduce exhaust emissions, generally NOx. Such nozzles have failed to attain adequate reduction of exhaust emissions. The present fuel injector structure has resulted in reduced NOx emissions. The structure includes a housing having a central axis and a bore coaxial therewith. An enlarged diameter portion of the housing has a plurality of swirler vanes positioned therein. A frustoconical blending portion is connected between the enlarged diameter portion and the bore. The structure further includes an angled passages intersecting with the bore and being tangent thereto. The unique structure swirls the air and fuel as they meet and mix within the bore. The angular velocity of the air and fuel are additive and provide the fuel injector nozzle with a structure that results in reduced NOx emissions.

Abstract: Most existing noise reduction enclosures used with engines and engine driven equipment have failed to meet the reduced noise emission requirements of today and of the future. A few of the present enclosures meet the reduced noise emission requirements of today and of the future but are extremely expensive to purchase and are large bulky structures. The subject enclosure (10) is reasonably priced and provides an enclosure which is effective in reducing the noise emitted therefrom. The enclosure (10) includes a housing (32) having a generally rectangular configuration and being divided into an engine portion (56) defining an engine compartment (57) and a duct portion (54). The outlet ducts (88) having a length greater than the inlet ducts (84). To further enhance the noise reduction of the enclosure (10) a plurality of dynastic hardware is attached to the housing (32).