Fluid reaction surfaces (i.e., impellers) inventions 05/08

20080124216 - Turbine blade assembly: A turbine blade assembly has a plurality of blades mounted on a central rotor. Each of the blades has a proximal section and a variable pitch section. A number of stays extend in groups from the central rotor to converge and terminate on an associated one of the blades. The... Agent: The Law Offices Of Thomas L. Adams

20080124225 - Turbine blade for a gas turbine, use of a turbine blade and method for cooling a turbine blade: There is described a turbine blade of a gas turbine comprising a suction-side blade wall and a pressure-side blade wall that, in the trailing edge area, runs toward the suction-side blade wall. This suction-side blade wall has a trailing edge projection projecting over the end edge of the pressure-side blade... Agent: Siemens Corporation Intellectual Property Department

20080124217 - Multi-turbine airflow amplifying generator: The wind generating device of the present invention employs modules each having two turbines. Each of the turbines employs two rotors, coaxially aligned and arranged one downstream from the other. The arrangement includes a proximal channel with a leading portion having decreasing radius toward the first rotor which acts as... Agent: G. Brian Pingel, Brown, Winick, Graves, Gross, Baskerville And Schoenebaum, P.L.C

20080124218 - Tip turbine egine comprising turbine clusters and radial attachment lock arrangement therefor: A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine... Agent: Carlson, Gaskey & Olds/pratt & Whitney

20080124220 - Lp turbine blade airfoil profile: A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an... Agent: Ogilvy Renault LLP (pwc)

20080124221 - Lp turbine vane airfoil profile: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an... Agent: Ogilvy Renault LLP (pwc)

20080124219 - Turbine exhaust strut airfoil profile: A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate... Agent: Ogilvy Renault LLP (pwc)

20080124222 - Heater assembly for deicing and/or anti-icing a component: A heater assembly for deicing and/or anti-icing a component includes a metallic heating element adjacent to a densely woven fabric layer impregnated with a resin that is capable of withstanding temperatures of up to 550° F. (288° C.).... Agent: Kinney & Lange, P.A.

20080124223 - Hp turbine vane airfoil profile: A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an... Agent: Ogilvy Renault LLP (pwc)

20080124224 - Shock mitigation suspension structure: A shock mitigation suspension structure of a ceiling fan, with the structure, vibrations and noise may be reduced. The shock mitigation suspension structure is used for hanging a ceiling fan on a ceiling, the ceiling fan has a pole; the shock mitigation suspension structure substantially includes a fixing frame, a... Agent: Hdsl

20080118353 - Sanitary removable impeller hub and method: A hub mounting assembly for mounting a plurality of impellers onto a shaft has a first hub ring and a second hub ring. A first key piece is adapted to engage with the shaft and engage with at least one of the hub rings, and a first lock pin is... Agent: Baker & Hostetler LLP

20080118354 - Wind turbine comprising a multiplied redundancy control system and method of controlling a wind turbine: A wind turbine (1) comprising equipment under control is presented, which comprises at least one control system (14, 14A, 14B) for one or more of said main components, (5, 7, 9) of the wind turbine. The control system (14A) is multiplied by at least one further control system (14B) for... Agent: Cantor Colburn, LLP

20080118355 - Turbine vane for turbo-machines and method for fabricating: A turbine blade for turbo-engines as well as a method for manufacturing such a turbine blade is disclosed. According to the task set, the turbine blades should be capable of withstanding high thermal stress and able to maintain an adequate mechanical strength even at raised operating temperatures. The turbine blades... Agent: Inco Patents & Licensing

20080118366 - Bifeed serpentine cooled blade: A turbine blade includes forward and aft serpentine cooling circuits terminating in corresponding forward and aft impingement channels. Each serpentine circuit has two metered inlets for distributing primary inlet flow to the first passes thereof and supplemental inlet flow to the last passes thereof.... Agent: Francis L. Conte, Esq.

20080118367 - Cooling of turbine blade suction tip rail: A turbine blade including an airfoil, the airfoil including an airfoil outer wall having pressure and suction sidewalls joined together at chordally spaced apart leading and trailing edges extending radially outwardly from a blade root to a blade tip surface. A continuous squealer tip rail extends radially outwardly from and... Agent: Siemens Corporation Intellectual Property Department

20080118356 - Hub for a horizontal axis wind turbine: To provide a lightweight hub of a horizontal axis wind turbine with a balanced strength, the hub 1 related to the present invention comprises a reinforcement plate 4 coupled to the spherical shell 2 on the peripheral edge in the round region G inside the circular flange 3 used to... Agent: Haynes And Boone, LLP

20080118357 - Turbofan and manufacturing method thereof: A turbofan integrally formed with a shroud and a method of manufacturing the same. The turbofan includes a rotating plate rotated by a driving motor, a plurality of blades having first ends connected to an outer peripheral portion of a front surface of the rotating plate while being arranged in... Agent: Stanzione & Kim, LLP

20080118361 - Hp turbine vane airfoil profile: A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an... Agent: Ogilvy Renault LLP (pwc)

20080118358 - Lp turbine blade airfoil profile: A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an... Agent: Ogilvy Renault LLP (pwc)

20080118360 - Lp turbine vane airfoil profile: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an... Agent: Ogilvy Renault LLP (pwc)

20080118362 - Transonic compressor rotors with non-monotonic meanline angle distributions: Airfoils are provided having non-monotonic meanline angle distributions and local negative camber along a length of the meanline between a point on a leading edge of the airfoil and a point on the trailing edge of the airfoil. The improved airfoil shape decreases the peak of a Mach number of... Agent: Siemens Corporation Intellectual Property Department

20080118359 - Turbine exhaust strut airfoil profile: A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate... Agent: Ogilvy Renault LLP (pwc)

20080118363 - Triforial tip cavity airfoil: A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.... Agent: Francis L. Conte, Esq.

20080118364 - Hp turbine blade airfoil profile: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an... Agent: Ogilvy Renault LLP (pwc)

20080118365 - Bulkhead of a wind turbine: A bulkhead for a wind turbine is provided. The wind turbine includes a rotor hub and a rotor blade operatively attached to the rotor hub. The rotor blade includes a blade root. The bulkhead includes multiple access openings with closable hatches and is arranged in or on the blade root... Agent: Rankin, Hill & Clark LLP

20080112807 - Methods and apparatus for operating a wind turbine: A method for operating a wind turbine having at least one blade includes determining an ambient air operating envelope and controlling a power output of the wind turbine at least partially based on the determined ambient air operating envelope. Determining an ambient air operating envelope includes measuring at least one... Agent: Patrick W. Rasche (22402)

20080112816 - Air-cooled component: A component such as a turbine blade of a gas turbine engine has a cooling arrangement comprising a cascade impingement array in which cooling air flows from a supply chamber through impingement passages in webs to an internal passageway comprising first and second limbs. The cooling air flow through the... Agent: Oliff & Berridge, Plc

20080112808 - Rotor system with pitch flap coupling: An articulated rotor system with a servo-flap rotor control system locates the focal point of a blade retention spherical elastomeric bearing inboard of a joint in the servo-flap pitch control tube which separates the flap hinge and supports the servo-flap pitch control tube on a single pivot bearing within a... Agent: Carlson, Gaskey & Olds, P.c.

20080112809 - Highly slenderness rotor: The present invention relates to a rotor for gas or steam turbines having a disk (1), an outer cover (2) and a plurality of blades (3). The disk (1) defines the portion of less diameter of the rotor and has an inner surface configured to be coupled on a shaft... Agent: Merchant & Gould Pc

20080112810 - Fan: A fan includes an impeller portion generating an air flow and a motor that rotates the impeller portion about a center axis. The impeller portion is attached to a yoke of a rotor portion of the motor and is rotated with the yoke. A circular portion of the impeller is... Agent: Nidec Corporation C/o Keating & Bennett, LLP

20080112811 - Hoop seal with partial slot geometry: A rotor blade assembly includes a slot for mounting a rotor blade that extends partially through a rotor disk and a continuous uninterrupted hoop seal that extends about the circumference of the rotor disk. The rotor disk includes an integrally formed seal that includes at least one knife edge disposed... Agent: Carlson, Gaskey & Olds/pratt & Whitney

20080112812 - Propeller blades propelling for all: Propeller blades without reverse rotating force and speed acceleration propeller blades are equipped in all kinds of transportations for accelerating speed without extra energy and generating transportation electricity.... Agent: Henri Duong

20080112813 - Rotor blade and wind energy plant: The present invention is related to rotor blade for a wind energy plant, with a blade root, with a first longitudinal portion starting from the blade root, with a second longitudinal portion, following up the first longitudinal portion and running into a blade tip, with a first surface, facing a... Agent: Vidas, Arrett & Steinkraus, P.a.

20080112814 - Method for the heat treatment of nickel-based superalloys: A heat treatment method for a nickel-based superalloy, in particular for the production of single-crystal components or directionally solidified components having a chemical composition permits full solution annealing at a temperature T1, the method comprising: partially solution annealing in a controlled manner at a temperature T2<T1 in a first step... Agent: Darby & Darby P.c.

20080112815 - Blade mounting ring for a turbocharger on an internal combustion engine: The invention relates to a blade mounting ring for a turbocharger with variable turbine geometry and turbine blades which may be adjusted in the blade mounting ring on an internal combustion engine for a motor vehicle, comprising an austenitic iron matrix alloy with a sulphur component to achieve a solid... Agent: Collard & Roe, P.c.

20080107527 - Ceiling fan: The invention relates generally to fans, and in particular to ceiling fans. The ceiling fan includes a motor with a shaft that rotates with the rotation of the motor. A fan blade assembly is coaxially coupled to the motor shaft. The motor and fan blade assembly are substantially remote to... Agent: Baker & Mckenzie LLP

20080107528 - Ceiling fan: A ceiling fan (10) is disclosed having a motor (13) and motor housing (11) suspended from a ceiling by a downrod (12). The motor rotatably drives an annular array of blades (15). The ceiling fan also includes a tubular screen or shroud (20) mounted about the motor housing and blades... Agent: Baker, Donelson, Bearman, Caldwell & Berkowitz

20080107541 - Refractory metal core main body trench: An article, such as a gas turbine engine turbine blade, includes a film cooling system having a trench recessed within a wall of the component, a passage that opens into the trench for discharging a coolant flow into the trench, and a guide member within the trench for influencing the... Agent: Carlson, Gaskey & Olds/pratt & Whitney

20080107526 - Apparatus and methods for handling rotor blades: An apparatus for handling rotor blades of wind power installations. An apparatus for simplified handling of rotor blades is afforded by a carrier element and at least one rotor blade receiving means fixedly connected thereto. A rotor blade is received in the apparatus during a blade fitting procedure. The apparatus... Agent: Seed Intellectual Property Law Group Pllc

20080107529 - Fan blade connector component with skeleton and method of manufacturing such: A fan blade connector component having a moldable ornamental housing that encloses a skeleton which includes links which span between adjacent posts having a threaded bore therein. The links include opposing side walls, a top wall, and a land therebetween. A plurality of spaced-apart openings extend through the top wall... Agent: Baker, Donelson, Bearman, Caldwell & Berkowitz

20080107530 - Coupling device for a turbine upstream guide vane, a turbine comprising same, and aircraft engine fitted therewith: f

20080107533 - System for manufacturing a rotor having an mmc ring component and a unitary airfoil component: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing blade conical surface; an airfoil component, wherein the at least one airfoil component has been created... Agent: Mcnees Wallace & Nurick Llc

20080107532 - System for manufacturing a rotor having an mmc ring component and an airfoil component having mmc airfoils: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing conical surface; an airfoil component, wherein the airfoil component further includes a plurality of individual airfoil... Agent: Mcnees Wallace & Nurick Llc

20080107531 - System for manufacturing a rotor having an mmc ring component and an airfoil component having monolithic airfoils: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a plurality of radially outwardly facing blade conical surfaces; an airfoil component, wherein the airfoil component further includes: a plurality of... Agent: Mcnees Wallace & Nurick Llc

20080107538 - swept turbomachine blade: The invention relates to a turbomachine blade comprising a plurality of blade sections stacked along a radial axis, and in which the projection of a line interconnecting the leading edges of the blade sections of the bottom stack onto a mid-plane presents a first longitudinal angle of inclination towards the... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.c.

20080107534 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080107535 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080107536 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080107537 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080107539 - Impeller manufacturing method and impeller: The present invention provides a manufacturing method for an impeller with which molding and high-quality finishing can be performed extremely easily and quickly through resin molding using a die, and an impeller manufactured by the impeller manufacturing method. A metallic bush is disposed in a die, whereupon a resin material... Agent: Mcginn Intellectual Property Law Group, Pllc

20080107540 - Damping element for a wind turbine rotor blade: A damping element for a wind turbine rotor blade is provided, the damping element comprising a laminate material made of at least one viscoelastic layer and at least one stiff layer adhered to said viscoelastic layer, wherein the damping element is adapted to be attached to a body of the... Agent: General Electric Co. Global Patent Operation

20080101961 - Turbine airfoil cooling system with spanwise equalizer rib: A cooling system for a turbine airfoil of a turbine engine having an inflow mid-chord feed channel and a trailing edge feed channel that are separated by an equalizer rib having a plurality of supply holes. The supply holes enable cooling fluids to be supplied to the trailing edge from... Agent: Siemens Corporation Intellectual Property Department

20080101930 - Wind turbine blade deflection control system: A wind turbine with a sensor that measures the out-of-plane deflection of the blades and a controller that uses the signal from the sensor to determine the risk of a tower strike. The controller takes any necessary action to prevent a tower strike when it determines that the risk of... Agent: John Vanden Bosche

20080101931 - Brushless direct current (bldc) motor based linear or rotary actuator for helicopter rotor control: A device for controlling the pitch of a helicopter's rotor blade, the device having a BLDC motor based actuator; and at least one control surface operatively connected to the BLDC motor based actuator. The actuator and the control surface are preferably fully integrated into the interior profile of the rotor... Agent: Carlson, Gaskey & Olds, P.C.

20080101932 - Wind driven power generator: The present invention is a wind driven power generator that has a rotational shroud assembly that has a base portion that is attached to a plurality of rotational base guides. A structure base has an annular shaped receiving rotational track that the rotational base guides rotate within. There is a... Agent: Teri G. Andrews Attorney At Law

20080101933 - Airflow generating apparatus: An airflow generating apparatus is provided. Fan blades are disposed around a hub, and one side of a fan blade is partially fixed on the peripheral of the hub, and another portion not fixed on the peripheral side of the hub is a free portion swinging with airflow. Therefore, the... Agent: Rabin & Berdo, PC

20080101934 - Assembly for providing flexure to blade system: An assembly for providing flexure to a blade of a rotary blade system includes an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned therebetween. At least one of the upper and lower yoke surfaces has a layer... Agent: Law Offices Of James E. Walton, PLLC

20080101935 - Variable compressor stator vane having extended fillet: An example variable stator vane assembly includes at least one button, a vane airfoil adjacent to the button, and a fillet defined between the button and the airfoil. In one example, the fillet defines a constant radius and extends beyond the button at least greater than a distance of 60%... Agent: Carlson, Gaskey & Olds/pratt & Whitney

20080101936 - Fan for vehicle: A fan for vehicle that considerably reduces noise and vibration by setting the center of gravity of a fan to agree with the rotational center of a fan without any additional means, such as adding a weight or frame thickness, by disposing blades at unequal angular intervals and providing the... Agent: Morgan, Lewis & Bockius LLP (sf)

20080101938 - Blade/disk dovetail backcut for blade/disk stress reduction (7fa, stage 1): A turbine blade that may include an airfoil and a blade dovetail, the blade dovetail being shaped corresponding to a dovetail slot in a turbine disk. The blade dovetail may include a dovetail backcut sized and positioned according to blade geometry to maximize a balance between stress reduction on the... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101939 - Blade/disk dovetail backcut for blade/disk stress reduction (7fa, stage 2): A turbine blade that may include an airfoil and a blade dovetail, the blade dovetail being shaped corresponding to a dovetail slot in a turbine disk. The blade dovetail may include a dovetail backcut sized and positioned according to blade geometry to maximize a balance between stress reduction on the... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101937 - Blade/disk dovetail backcut for blade/disk stress reduction (9fa, stage 1): A turbine blade that may include an airfoil and a blade dovetail, the blade dovetail being shaped corresponding to a dovetail slot in a turbine disk. The blade dovetail may include a dovetail backcut sized and positioned according to blade geometry to maximize a balance between stress reduction on the... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101940 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101941 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101942 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101943 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101944 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101945 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101946 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101947 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101948 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101949 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101950 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101951 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101952 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101953 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101954 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101955 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101956 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101957 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101958 - Airfoil shape for a compressor: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in... Agent: Ge Energy General Electric C/o Ernest G. Cusick

20080101959 - Rotor blade profile optimization: An airfoil for a rotor blade including an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z to facilitate balancing performance and durability of the rotor blade and to facilitate improving an operating efficiency of a high-pressure turbine is provided. The profile is carried only... Agent: John S. Beulick (12729) C/o Armstrong Teasdale LLP

20080101960 - Blades: A blade for a gas turbine engine includes a root portion, an aerofoil portion and a transition portion between the root portion and the aerofoil portion. The aerofoil portions and the transition portion are defined by first and second wall members, the first and second wall members being secured together... Agent: Oliff & Berridge, PLC