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| Number | Title | Issue Date |
| 5845479 | Method for providing emergency reserve power using storage techniques for electrical systems applications A combustion turbine power generation system includes a modified simple cycle combustion turbine power generation system optimized for a "hot" stand-by reserve mode of operation and having a power shaft assembly including a compressor, an expansion turbin... | 12/08/1998 |
| 5444971 | Method and apparatus for cooling the inlet air of gas turbine and internal combustion engine prime movers A multi-stage method and apparatus for cooling the inlet air of internal combustion engine and gas turbine prime movers with various load applications comprising: generating and providing a multi-stage refrigerated cooling system associated with the air i... | 08/29/1995 |
| 5381655 | Admission mixing duct assembly A variable cycle jet engine is provided with a mixing duct assembly which mixes core engine exhaust gas with bypass air when the engine is operating in a turbofan mode and which blocks flow from the core engine and isolates the core engine from the bypass... | 01/17/1995 |
| 5375420 | Segmented centerbody for a double annular combustor A double annular combustor having concentrically disposed inner and outer annular combustors is provided with inner and outer domes. A centerbody is disposed between the inner and outer domes and is constructed of a plurality of annular segments. Each seg... | 12/27/1994 |
| 5372008 | Lean premix combustor system 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 p... | 12/13/1994 |
| 5363654 | Recuperative impingement cooling of jet engine components Impingement cooling of a jet engine subassembly, such as a combustor. Adjacent raised corrugation portions and intervening plate portions (having impingement cooling holes) of a corrugated plate define coolant channels in fluid communication with the engi... | 11/15/1994 |
| 5361586 | Gas turbine ultra low NOx combustor A gas turbine combustor having a pre-mixing zone and a combustion zone separated by a barrier plate. A plurality of concentrically arranged annular passages, into which lean mixtures of fuel and air are introduced, are disposed in the pre-mixing zone. Eac... | 11/08/1994 |
| 5361578 | Gas turbine dual fuel nozzle assembly with steam injection capability A fuel nozzle assembly is provided having the capability of burning either gaseous or liquid fuel, or both simultaneously, along with steam injection. The nozzle has a nozzle body that is attached to a nozzle cap by inner, outer and middle sleeves. The sl... | 11/08/1994 |
| 5361581 | Pulsed piston-compressor jet engine An air-breathing pulsed jet engine for aircraft propulsion which employs a piston compressor rather than much more expensive axial or centrifugal compressors and turbines employed by conventional turbojet engines. The engine is similar to the common two-c... | 11/08/1994 |
| 5359847 | Dual fuel ultra-low NOX combustor An ultra-low NOx gas turbine combustor having a dual fuel capability. The combustor has a pre-mixing zone and a downstream combustion zone. The pre-mixing zone has three concentric annular passages that surround a central diffusion-type dual fuel nozzle. ... | 11/01/1994 |
| 5359850 | Self venting carbon or graphite phenolic ablatives Self venting ablative carbon or graphite composite materials are prepared by interspersing low temperature degradable thread within the woven carbon or graphite cloth prior to impregnation with a phenolic or resin matrix. The degradable threads do not deg... | 11/01/1994 |
| 5357744 | Segmented turbine flowpath assembly A turbine flowpath assembly includes a plurality of circumferentially spaced apart airfoils disposed within an annular outer casing. Each of the airfoils includes outer and inner integral bands. A plurality of flowpath outer and inner panels are disposed ... | 10/25/1994 |
| 5355670 | Cartridge assembly for supplying water to a fuel nozzle body A breech loaded fuel nozzle cartridge assembly is provided for use with a fuel nozzle capable of use with gaseous or distillate fuels. The cartridge assembly includes an elongated water delivery pipe having an interior through passageway extending from a ... | 10/18/1994 |
| 5353599 | Fuel nozzle swirler for combustors The swirler for the fuel nozzle of the combustor of a gas turbine engine in engine designs where the swirler is off set from the center line of the combustor, localized erosion is obviated by locating and angling air cooling holes around the air swirler b... | 10/11/1994 |
| 5351489 | Fuel jetting nozzle assembly for use in gas turbine combustor A fuel jetting nozzle assembly for use in a gas turbine combustor comprises a nozzle head secured to a head plate, a fuel jetting nozzle secured to the nozzle head and having fuel jetting holes opened to an inside of a combustion chamber, swirling vanes d... | 10/04/1994 |
| 5345768 | Dual-fuel pre-mixing burner assembly The burner assembly includes a flow body 12 having a central liquid fuel injection nozzle 14, inner and outer concentric passages 24 and 26, respectively, and a flow duct comprising a venturi downstream of the liquid injection nozzle. The inner passage 24... | 09/13/1994 |
| 5343697 | Variable area bypass injector A variable area bypass injector (VABI) for a variable cycle gas turbine engine includes a circumferentially continuous valve with a conical surface sloping into a screech suppressor surface, a circumferentially segmented seal attached to the diffuser, and... | 09/06/1994 |
| 5345148 | DC-AC converter for igniting and supplying a gas discharge lamp A DC-AC converter for igniting and supplying a gas discharge lamp comprises a converter control circuit including a starter circuit containing first, second and third switching elements; a load circuit including at least one gas discharge lamp; and an ign... | 09/06/1994 |
| 5343693 | Combustor and method of operating the same A combustor comprises a passage area changing mechanism which relatively moves a flame holder relative to a premixed combustion nozzle in an axial direction so that the area of passage for premixed gas between an injection edge of the premixed combustion ... | 09/06/1994 |
| 5340286 | Balanced turbocharger A combination turbine and air compressor apparatus comprises a housing having first and second air inlet and first and second compressed air outlets, an operating gas inlet, and an operating gas outlet. Ends of a turbine-air compressor shaft are rotatably... | 08/23/1994 |
| 5339623 | Singly fueled multiple thrusters simultaneously energized by a common power supply A spacecraft has, in addition to redundant thrusters T3, T4 prime thrusters T1 or T2 arranged to be operated one at a time which are supplied with propellant 1 via valves V1 and V2. The thrusters are of the kind in which energy is transferred to the prope... | 08/23/1994 |
| 5339635 | Gas turbine combustor of the completely premixed combustion type A gas turbine combustor of the pre-mixed combustion system in which the pre-mixed fuel and the air are combusted. The gas turbine combustor comprises main cylindrical nozzles provided in the end wall on the upstream side of a cylindrical combustion chambe... | 08/23/1994 |
| 5339625 | Hybrid rocket motor solid fuel grain A hybrid rocket motor includes a solid propellant fuel grain component which incorporates fuel strengthening agents or mechanical retention devices. In one embodiment, the hybrid fuel formulation is a modified elastomeric polyurethane reaction product bas... | 08/23/1994 |
| 5339634 | Fuel supply system for engines and combustion processes therefor An engine is provided which, in at least one cylinder or combustion area, is provided with a hydrocarbon rich fuel which produces upon combustion an exhaust gas containing unburned hydrocarbons, water vapor and carbon monoxide. The exhaust gas is treated ... | 08/23/1994 |
| 5337568 | Micro-grooved heat transfer wall A gas turbine engine hot section component such as a turbine blade or vane having an airfoil is provided a non-film cooled portion of a heat transfer wall having a hot surface and a plurality of longitudinally extending micro-grooves disposed in the porti... | 08/16/1994 |
| 5335502 | Arched combustor A gas turbine engine combustor includes radially spaced outer and inner liners disposed coaxially about an engine longitudinal centerline axis with each liner having forward and aft ends. An annular dome is fixedly joined to the forward ends of the outer ... | 08/09/1994 |
| 5335491 | Combustion chamber with axially displaced fuel injectors A generally annular combustion chamber for a gas turbine engine is disclosed in which a plurality of generally cylindrical walls extend forwardly from an upstream end wall of the combustion chamber such that each cylindrical wall defines a cavity which is... | 08/09/1994 |
| 5336053 | Method of testing for leakage in a solution pumping system A method of testing a pumping system including a pump cassette effects pressurization of the system, with subsequent monitoring of any pressure loss in the system. This is achieved by closing any inlets and outlets of the cassette, and thereafter over-pre... | 08/09/1994 |
| 5331816 | Gas turbine engine combustor fiber reinforced glass ceramic matrix liner with embedded refractory ceramic tiles A gas turbine engine combustor liner with improved high temperature capability is achieved by embedding ceramic tiles into a fiber reinforced glass ceramic matrix composite substrate, so as to incorporate a space between the tiles and the substrate, the s... | 07/26/1994 |
| 5331814 | Gas turbine combustion chamber with multiple fuel injector arrays A gas turbine engine combustion chamber is disclosed having multiple sets of fuel injectors. A set of first fuel injectors are arranged in two radially inner and outer generally circular first arrays such that the fuel injectors of one array are located c... | 07/26/1994 |
| 5331805 | Reduced diameter annular combustor An annular gas turbine engine combustor includes additional axial primary airflow openings, formed as arcuately segmented openings on opposite sides of each of the airblast fuel nozzles of the combustor, for reducing overall combustor diameter while maint... | 07/26/1994 |
| 5331806 | Hydrogen fuelled gas turbine A hydrogen fuelled gas turbine which includes a combustion chamber having a steam inlet, an oxygen inlet, a hydrogen inlet, and an outlet. A compressor is provided. The steam inlet is connected to the compressor such that the compressor provides steam as ... | 07/26/1994 |
| 5327727 | Micro-grooved heat transfer combustor wall A gas turbine engine hot section combustor liner is provided a non-film cooled portion of a heat transfer wall having a hot surface and a plurality of longitudinally extending micro-grooves disposed in the portion of the wall along the hot surface in a di... | 07/12/1994 |
| 5323606 | Stowable nozzle A vectorable nozzle for directing the thrust produced by a gas turbine engine includes a duct, at least one toroidal nozzle segment, and a carrier ring for mounting the nozzle segment to the duct. The nozzle segment is hinged to the outer circumferential ... | 06/28/1994 |
| 5323604 | Triple annular combustor for gas turbine engine In accordance with one aspect of the present invention, a combustor is disclosed having three separate domes, each dome having disposed therein a plurality of circumferentially spaced mixers for uniformly mixing air and fuel. The combustor utilizes a high... | 06/28/1994 |
| 5323605 | Double dome arched combustor A gas turbine engine combustor includes radially spaced outer and inner liners disposed coaxially about an engine longitudinal centerline axis with each liner having forward and aft ends. An annular dome is fixedly joined to the forward ends of the outer ... | 06/28/1994 |
| 5323600 | Liner stop assembly for a combustor The liner stop assembly includes a flow sleeve stop, a liner stop, an adjuster, a lock plate and a bolt. The flow sleeve stop and liner stop have radial projections which axially butt one another upon insertion of the liner into the flow sleeve. The flow ... | 06/28/1994 |
| 5321947 | Lean premix combustion system having reduced combustion pressure oscillation 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 pres... | 06/21/1994 |
| 5321950 | Air assist fuel injection system In order to achieve ignition at altitude, particularly in relatively small combustors (10) with low fuel flow rates, a fuel injection system (20) includes an air nozzle (26), a fuel nozzle (28), and an air assist tube (34). The fuel nozzle (28) is dispose... | 06/21/1994 |
| 5321951 | Integral combustor splash plate and sleeve A carburetor for the combustor of a gas turbine engine wherein a swirler and a venturi cooperate to atomize and mix air and fuel for the combustor, wherein a downstream mounted integrally formed sleeve and splash plate is provided to control the flow of t... | 06/21/1994 |
