| Patent Number |
Title Of Patent |
Date Issued |
| RE39630 |
Turbine blisk rim friction finger damper |
May 15, 2007 |
| A damper for reducing vibrations in an integrally bladed turbine disk is provided. The damper includes an annular member and a plurality of fingers. The annular member is configured so that it is coupled to a face of the integrally bladed turbine disk. The plurality of fingers are ci |
| RE38040 |
Swept turbomachinery blade |
March 18, 2003 |
| A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages |
| RE36926 |
Welding control using fuzzy logic analysis of video imaged puddle dimensions |
October 31, 2000 |
| A welding system includes an imaging system that takes frame by frame pictures of a weld puddle. The imaging system is located in the weld torch. From the images puddle length and width are determined. The length and width are applied against stored membership functions that cover a |
| RE36117 |
Vanadium corrosion inhibitor |
March 2, 1999 |
| A corrosion inhibited fuel mixture includes a hydrocarbon fuel, at least one vanadium composition, and a yttrium composition. The concentration of the yttrium composition in the mixture provides at least a stoichiometric amount of yttrium for a substantially complete reaction between the |
| RE35962 |
Single longitudinal mode pumped optical waveguide laser arrangement |
November 17, 1998 |
| An optical waveguide laser arrangement includes a solid optical waveguide having a waveguiding portion that extends along an axis between two spaced regions of the optical waveguide and is of a material capable of emitting stimulated light upon excitation by pumping light that is launche |
| RE33954 |
Rotor blade assembly |
June 9, 1992 |
| Rotor blade and disk structures enabling the disassembly and reassembly of a single rotor blade are disclosed. The concepts are particularly suited to configurations employing interlocking mid-span shrouds which inhibit the withdrawal of a single blade from a disk.In one specific geometr |
| RE33876 |
Thermal barrier coating for nickel and cobalt base super alloys |
April 7, 1992 |
| Adherent, thermal shock-resistant protective coatings for nickel base super alloys are obtained by applying to the base metal a thin bond coat of an alloy of chromium aluminum and yttrium with materials selected from the group consisting of iron, cobalt, nickel and nickel-cobalt and appl |
| RE33800 |
Method for electroplating nickel onto titanium alloys |
January 21, 1992 |
| This invention relates to an improved method for electroplating a layer of nickel into titanium base alloy substrates. It is particularly useful in electroplating a layer of nickel onto titanium alloys which contain refractory metal elements, such as the alloy Ti-8Al-1V-1Mo. The method |
| RE33589 |
Helicopter blade airfoil |
May 14, 1991 |
| A family of airfoil cross sections, termed SC21xx, for use in a helicopter blade is disclosed. The airfoil (36) achieves maximum lift performance equivalent to prior art airfoil configurations without incurring increased aerodynamic drag at high velocities. The airfoil (36) was developed |
| RE33087 |
Electric power distribution and load transfer system |
October 10, 1989 |
| A power distribution system includes a plurality of power sources and load transfer units including transistors and diodes connected in series and leading to a common power output, each of the transistors being controller switchable subject to voltage levels of the respective input and o |
| RE32339 |
Blade to blade vibration damper |
January 27, 1987 |
| Effective damping of blade vibratory energy is sought by the apparatus described herein. The concepts relate specifically to what is known as blade to blade damping as is distinguished from blade to ground damping.The dampers employed have a "T" shaped cross section geometry and are desi |
| RE32121 |
Overlay coatings for superalloys |
April 22, 1986 |
| Improved coating compositions are described for the protection of superalloys at elevated temperatures. The coatings are of the MCrAlY type where M is nickel or cobalt and are significantly improved by the addition of from 0.1-7% silicon and 0.1-2% hafnium. Coatings of the invention are |
| RE32100 |
Efficiency air cycle environmental control system |
April 1, 1986 |
| In a compressed air powered refrigeration system for aircraft containing a refrigeration turbine and associated heat exchangers for supplying cool air to the aircraft cabin, air is recirculated from the cabin by a recirculation means and combined with the turbine discharge air to sim |
| RE31835 |
Pneumatic supply system having variable geometry compressor |
February 19, 1985 |
| In a compressed air supply system utilizing a shaft-driven compressor (10,16), the flow capacity of the compressor is changed by varying the compressor outlet stator geometry (16) by an actuator (18) which controls the outlet stator geometry to provide an optimum match between the co |
| RE31823 |
Chemical milling of high tungsten content superalloys |
February 5, 1985 |
| Chemical milling of cast superalloys having high tungsten contents is advantageously accomplished with an etchant which consists by volume percent of 40-60 concentrated HNO.sub.3, 0.6-0.8 concentrated HF, .[.30.]..Iadd.40.Iaddend.-70 H.sub.2 O, with which is included at least 0.008 m |
| RE31605 |
Method and apparatus for electrochemically finishing airfoil edges |
June 19, 1984 |
| Disclosed is apparatus and method for electrochemically finishing the edges of airfoils and other thin edged objects. When the edge on an airfoil varies in thickness along its length, a tapered electrode is provided which has both a decreased diameter and increased spacing distance, |
| RE30210 |
Damped intershaft bearing and stabilizer |
February 12, 1980 |
| A viscous damper for a bearing mounted between coaxially mounted shafts rotating at relative speeds is stabilized by mounting a spring in parallel with the damper so as to raise the natural frequency of one of the shafts. |
| RE30160 |
Smoke reduction combustion chamber |
November 27, 1979 |
| A combustion chamber either an annular or can-annular type, which substantially eliminates the production of smoke while maintaining all other performance parameters of the combustion chamber. The combustion chamber is provided with a front end configuration which substantially elimi |
| RE29667 |
Compressor surge sensor |
June 13, 1978 |
| The disclosure of this invention relates to means for detecting compressor surge by sensing the pressure downstream of the compressor of a turbine type power plant for rapidly opening the compressor bleeds and holding the bleeds open for brief interval after surge disappears. The sensed |
| H1207 |
Chromic acid anodization of titanium |
July 6, 1993 |
| The present invention discloses a method of forming an adhesion promoting oxide surface on titanium in which the titanium surface is first abraded and then anodized in hydrofluoric acid free chromic acid. |
| D409810 |
Combined transportable assembly workstation and turbine blade storage container |
May 11, 1999 |
|
| D371732 |
Attachment tool for a system for repairing damaged gas turbine engine airfoils |
July 16, 1996 |
|
| D361053 |
Helicopter |
August 8, 1995 |
|
| D336888 |
Helicopter |
June 29, 1993 |
|
| D304122 |
Tote box |
October 17, 1989 |
|
| D297005 |
Helicopter |
August 2, 1988 |
|
| D284662 |
Hotel telephone faceplate |
July 15, 1986 |
|
| D242991 |
Electrical current probe |
January 11, 1977 |
|
| D242722 |
Housing for motor vehicle diagnostic equipment |
December 14, 1976 |
|
| 7618514 |
Photo-etched EDM electrode |
November 17, 2009 |
| An electrical discharge machining electrode includes a body and one or more shaped teeth. The one or more shaped teeth of the body have a diffuser section and a metering section in electrical communication therewith. The body and the teeth may be formed by a process of photochemicall |
| 7617685 |
Quick change fastener system for attaching liner bracket to convergent flap and seal in turbine |
November 17, 2009 |
| A quick change connection is provided for attaching a bracket and liner subassembly to convergent flaps and seals in an adjustable nozzle for a gas turbine engine. A threaded attachment member has a t-shaped head that is secured to prevent rotation by a washer. The washer is held in plac |
| 7617029 |
System and method for fault code driven maintenance system |
November 10, 2009 |
| A system, program instructions or method for maintaining a deployed product having at least one component, as well as training of the maintenance workers, is provided. The system has a microserver, a sensor and an electronic device. The microserver is integral with the deployed produ |
| 7615104 |
Fuel deoxygenation system with multi-layer oxygen permeable membrane |
November 10, 2009 |
| A fuel system for an energy conversion device includes a deoxygenator system with an oxygen permeable membrane formed from a multiple of layers. The layers include a sealant layer, an oxygen permeability layer and a porous backing layer. The layered composite oxygen permeable membran |
| 7614848 |
Fan exit guide vane repair method and apparatus |
November 10, 2009 |
| A replacement fan exit guide vane assembly for installation between an inner case and an outer case of a gas turbine engine includes an airfoil structure having an outer end and an inner end, a wedge structure connected to the outer end of the airfoil structure, a base plate position |
| 7614235 |
Combustor cooling hole pattern |
November 10, 2009 |
| A combustor assembly includes an inner and outer liner defining a combustion chamber. The inner and outer liners include a plurality of cooling holes spaced a specified distance apart. The cooling holes include first, second and third groups. The first group of cooling holes is the m |
| 7610763 |
Tailorable design configuration topologies for aircraft engine mid-turbine frames |
November 3, 2009 |
| A mid-turbine frame has a pre-stress design and is connected to an engine casing of a jet turbine engine to distribute a first load from a first bearing and a second load from a second bearing. The mid-turbine frame includes at least one torque box, a first bearing, a second bearing, and |
| 7610179 |
Coupled parametric design of flow control and duct shape |
October 27, 2009 |
| A method for designing gas turbine engine components using a coupled parametric analysis of part geometry and flow control is disclosed. Included are the steps of parametrically defining the geometry of the duct wall shape, parametrically defining one or more flow control actuators i |
| 7607891 |
Turbine component with tip flagged pedestal cooling |
October 27, 2009 |
| A turbine blade for a gas turbine engine is provided with improved cooling at a radially outer portion of the trailing edge. A tip flag path is provided with a first pedestal array to increase the heat transfer at the area. In addition, a second pedestal array replaces the metering holes |
| 7607890 |
Robust microcircuits for turbine airfoils |
October 27, 2009 |
| A cooling microcircuit for use in a turbine engine component, such as a turbine blade, having an airfoil portion is provided. The cooling microcircuit has at least one inlet slot for introducing a flow of coolant into the cooling microcircuit, a plurality of fluid exit slots for dist |
| 7607287 |
Airfoil acoustic impedance control |
October 27, 2009 |
| A noise control cassette for a gas turbine engine includes a perforated face sheet configured for exposure to an airflow, a non-perforated backing sheet, a core arranged between the face sheet and the backing sheet and defining a cavity between the face sheet and the backing sheet ha |
| 7607286 |
Regenerative turbine blade and vane cooling for a tip turbine engine |
October 27, 2009 |
| A fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage (80) |
| 7603890 |
Method of inspecting a metal alloy part for incipient melting |
October 20, 2009 |
| A method of inspecting a repaired metal alloy part to analyze a microstructure of the metal part includes placing a replicating material on a surface of the metal part to create an inverted replica of the microstructure. The replicating material is then removed from the surface. An i |
| 7601203 |
Hybrid vacuum system for fuel deoxygenation |
October 13, 2009 |
| A fuel system for a gas turbine engine removes oxygen from fuel with a fuel stabilization unit (FSU). The FSU includes a first vacuum stage, where vacuum pressure is created by an ejector and a second vacuum stage where vacuum pressure is created by the ejector and a vacuum pump. The |
| 7600967 |
Stator assembly, module and method for forming a rotary machine |
October 13, 2009 |
| A stator assembly for a rotary machine having an array of wall segments for bounding a working medium flow path is disclosed. Various construction details which provide a sealing structure for the segments are developed. In one detailed embodiment, a removable seal retainer for a sea |
| 7600966 |
Turbine airfoil with improved cooling |
October 13, 2009 |
| A turbine airfoil includes an outer wall and a plurality of cooling passages or minicores formed in the outer wall. A web separates each adjacent pair of the minicores. In order to provide more effective, even cooling of the airfoil, a baffle inside the airfoil includes a plurality o |
| 7596954 |
Blade clearance control |
October 6, 2009 |
| A turbine engine has a circumferentially segmented shroud within a case structure. Each shroud segment is mounted for movement between an inboard position and an outboard position. One or more springs bias the shroud segments toward their inboard positions. One or more valves are pos |
| 7594794 |
Leaned high pressure compressor inlet guide vane |
September 29, 2009 |
| A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades |
| 7594405 |
Catenary mid-turbine frame design |
September 29, 2009 |
| An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has an exterior surface and an interior surface. A plurality dimples are formed in the engine |
| 7594404 |
Embedded mount for mid-turbine frame |
September 29, 2009 |
| An engine casing for a mid-turbine frame having a plurality of radially extending struts includes a ring structure and at least one mount. The ring structure has an interior surface, an exterior surface, and a plurality of equally spaced dimples along the exterior surface and protrud |
| 7591754 |
Epicyclic gear train integral sun gear coupling design |
September 22, 2009 |
| A coupling system for connecting a sun gear to a shaft within a planetary gear train, includes a sun gear coupling connecting the sun gear to the shaft. The sun gear coupling has at least one undulant flexible section joined to an inflexible spindle for accommodating misalignment between |
