Patent application number | Description | Published |
20080211192 | Blade outer air seal - A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions. | 09-04-2008 |
20090010765 | Reinforced Airfoils - A reinforced airfoil includes an airfoil body including opposed walls that define a hollow interior space and a reinforcement member provided on at least one of the walls within the interior space, the reinforcement member increasing the thickness of the at least one wall so as to resist deformation of the at least one wall but not extending from one wall to the other. | 01-08-2009 |
20090028702 | BLADE COOLING PASSAGE FOR A TURBINE ENGINE - A blade for a turbine engine includes structure providing spaced apart suction and pressure sides. A cooling passage includes a first passageway near the pressure side and a second passageway in fluid communication with the first passageway. The second passageway is arranged between the first passageway and the suction side. The cooling passage provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges of the blade. During use, cooling fluid is supplied to the pressure side through first cooling apertures fluidly connected to the first passageway to the suction side through second cooling apertures fluidly connected to the other passage way. The first passageway is at a higher pressure that then second passageway so that cooling fluid is provided by the cooling passage to the pressure and suction sides in a balanced fashion. | 01-29-2009 |
20090044512 | DIRT SEPARATOR FOR COMPRESSOR DIFFUSER IN GAS TURBINE ENGINE - A compressor diffuser for a gas turbine engine is provided with a dirt separator. The dirt separator ensures the air having moved downstream of the compressor section, and moving toward the combustion section, is separated into a dirtier air flow path directly radially outwardly, and a cleaner airflow path directed radially inwardly. In this manner, the air reaching a combustion section, and the air being utilized for radially inner cooling air is relatively cleaner air. Further, the dirt separator provides a convenient surface for mounting a pressure sensor. In one embodiment, the dirt separator is mounted within the diffuser housing, and in a second embodiment, it is mounted immediately downstream. | 02-19-2009 |
20090060741 | TURBINE ENGINE BLADE COOLING - A blade is provided for a turbine engine that includes an exterior surface. The exterior surface includes a portion having a thermal barrier coating and an uncoated shelf adjacent to the thermal barrier coating without the thermal barrier coating. A cooling hole extends from an internal passageway through the exterior surface to an exit. A scarfed channel is recessed in the exterior surface and interconnected to the cooling hole at the exit. The scarfed channel extends to a blade tip end surface. The scarfed channel protects the cooling fluid exiting the cooling hole from secondary flows surrounding the blade that would otherwise mix with and disperse the cooling fluid. The scarfed channels also increase the surface area exposed to the cooling fluid to increase the heat transfer rate. | 03-05-2009 |
20090067994 | Blade outer air seal - A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions. | 03-12-2009 |
20090116956 | MANUFACTURABLE AND INSPECTABLE COOLING MICROCIRCUITS FOR BLADE-OUTER-AIR-SEALS - A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls. | 05-07-2009 |
20090285683 | Triangular serpentine cooling channels - A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and cooling channels extending radially between the base and the tip of the airfoil between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply through the base of the airfoil. The cooling channels include a leading edge channel, a trailing edge channel, a serpentine cooling circuit, and a dedicated up-pass channel. The serpentine cooling circuit includes a first up-pass channel forward of the trailing edge channel and configured to be in flow communication with a supply channel through the base of the airfoil, a down-pass channel forward of and in flow communication with the first up-pass channel, and a second up-pass channel forward of and in flow communication with the down-pass channel. At least the down-pass channel and the second up-pass channel of the serpentine circuit have a generally triangular transverse cross-sectional shape. The dedicated up-pass channel is arranged between the leading edge channel and the second up-pass channel of the serpentine cooling circuit. | 11-19-2009 |
20090285684 | Turbine blade internal cooling configuration - A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit. | 11-19-2009 |
20110132876 | ARTICLE HAVING DIFFUSER HOLES AND METHOD OF MAKING SAME - The diffusion opening in the cooling hole of an airfoil is formed by an EDM process in which the outwardly flaring sidewalls of the opening, rather then having surfaces that are approximated to be smooth by having many small ribs formed therein, are formed with a relatively few ribs with both longitudinally extending and radially extending surfaces that are substantially greater in dimension than those as normally formed. In this manner, the machining process is simplified and expedited, while at the same time, the cooling efficiency is increased. | 06-09-2011 |
20110135446 | Castings, Casting Cores, and Methods - If a refractory metal core (RMC) is punched, the punching asymmetry may be reflected in an asymmetry of the cast article features cast by the punched features. The punched features may have a shear zone and a fracture zone. The shear zone of the RMC will cast a relatively narrow portion of the post near one end; whereas the fracture zone will cast a relatively broader portion near the other end. The broader portion will also have a relatively shallow transition to the adjacent face of the slot-like passageway cast by the RMC. Where there is a stress asymmetry in the cast article in-use, the punching direction may be chosen so that the relatively broad portions of the post fall along the relatively higher stress face of the passageway. | 06-09-2011 |
20110186550 | METHOD OF CREATING AN AIRFOIL TRENCH AND A PLURALITY OF COOLING HOLES WITHIN THE TRENCH - A tool for forming a trench and a plurality of cooling holes within the trench includes a body, the body including a ridge portion extending along a first side of the tool. The ridge portion is operable to mate with a workpiece to form a trench on the workpiece. A plurality of electrodes extend from the ridge portion and are oriented to form a plurality of cooling holes within the trench on the workpiece. | 08-04-2011 |
20130001203 | ELECTRIC DISCHARGE MACHINING HOLE DRILLING - An apparatus and method for machining apertures into a conductive workpiece is disclosed. The apparatus has a tank capable of holding a dielectric fluid, and a fixture for holding the workpiece in the tank. An electric discharge machine with an electrode, a power supply connected to the electrode that produces machining pulses for electric discharge machining through the workpiece, and a controller for regulating the power supply and electrode position is also part of the apparatus. Finally, the apparatus has a pressure transducer connected to the fixture, and a process controller in communication with the electric discharge machine controller and pressure transducer. | 01-03-2013 |
20130039773 | METHOD OF MEASURING TURBINE BLADE TIP EROSION - A method of designing a turbine blade includes the steps of forming at least two notches on a tip of a turbine blade, each of the at least two notches having a known dimension. The turbine blade has a pressure side and a suction side. The method further includes the step of operating a gas turbine engine including the turbine blade to expand a length of the turbine blade such that the tip of the turbine engages a casing. The method further includes the steps of viewing the tip of the turbine blade after the step of operating of the gas turbine engine, determining an appearance of the notches on the tip and determining a manufacturing length of the turbine blade based on the step of determining the appearance the notches. | 02-14-2013 |
20130156601 | GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT - An airfoil for a gas turbine engine includes an airfoil body and a cooling circuit defined within the airfoil body. The cooling circuit includes at least a first cavity in fluid communication with a second cavity. A first portion of the first cavity extends between an outer diameter and an inner diameter of the airfoil body and a second portion of the first cavity extends across a space between a leading edge and a trailing edge of the airfoil body. | 06-20-2013 |
20130170963 | HYBRID BLADE OUTER AIR SEAL FOR GAS TURBINE ENGINE - A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face. | 07-04-2013 |
20130205802 | COOLING HOLE WITH CRENELLATION FEATURES - A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface and a diffusing section in communication with the inlet and extending to the outlet. The diffusing section includes a plurality of crenellation features that encourage lateral spreading of cooling air flowing through the cooling hole. | 08-15-2013 |
20130206733 | EDM METHOD FOR MULTI-LOBED COOLING HOLE - A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges. | 08-15-2013 |
20130209232 | MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS - A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed. | 08-15-2013 |
20130243591 | GAS TURBINE ENGINE AIRFOIL COOLING CIRCUIT - An airfoil for a gas turbine engine according to one exemplary embodiment includes an airfoil body that extends between a leading edge and a trailing edge. A cooling circuit can be defined within the airfoil body. The cooling circuit can include at least one trip strip disposed within a cavity of the cooling circuit between a leading edge inner wall and a first rib. The at least one trip strip can include an increasing height in a direction from the first rib toward the leading edge inner wall. | 09-19-2013 |
20130251536 | HYBRID AIRFOIL FOR A GAS TURBINE ENGINE - A hybrid airfoil for a gas turbine engine according to an exemplary embodiment of this disclosure can include a leading edge portion, a trailing edge portion, and an intermediate portion between the leading edge portion and the trailing edge portion. The leading edge portion can be made of a first material, the trailing edge portion can be made of a second material, and the intermediate portion can be made of a third material. At least two of the first material, the second material and the third material are different materials. | 09-26-2013 |
20140072436 | TURBINE AIRFOIL PLATFORM RAIL WITH GUSSET - A blade for a gas turbine engine includes a shank interconnecting a root and a platform, and an airfoil extending radially from the shank. The shank includes a pocket with the platform overhanging the pocket. A rail extends axially along a lateral edge of the platform and extends radially inward from the platform in a direction opposite the airfoil. A gusset extends from an underside of the platform facing the pocket and in a circumferential direction between the rail and the shank. | 03-13-2014 |
20140137407 | METHOD OF EXTENDING LIFE OF ROTATING PARTS - A method of refurbishing a gas turbine engine rotor is disclosed and includes an initial step of inspecting a rotor for defects such as cracks. A strain is then generated around any detected cracks in the rotor to create enhanced plasticized zones about the detected defects that delay defect propagation. Strain is generated by rotating the rotor at speeds greater than operational speeds to induce the desired strain and delay the propagation of defects. | 05-22-2014 |
20140183164 | NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINING SYSTEM - An electro discharge machining system includes a guide having first and second portions that are non-colinear with respect to one another. A consumable electrode is housed within the guide and configured to drill cooling holes in a component. A controller is programmed to position the guide and electrode to a desired position with respect to the component. An electro discharge machining guide includes first and second portions that are non-colinear with respect to one another and that include a passage configured to receive an electrode. | 07-03-2014 |
20140186164 | NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART - A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening. | 07-03-2014 |
20140193246 | COOLING HOLE WITH CRENELLATION FEATURES - A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region. | 07-10-2014 |
20140208771 | GAS TURBINE ENGINE COMPONENT COOLING ARRANGEMENT - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion having an exterior surface and an internal surface. A cavity is disposed inside of the body portion. A cooling hole extends between the exterior surface and the internal surface and includes a metering section having an outlet and an inlet. The inlet is shaped dissimilar to the outlet. | 07-31-2014 |
20140212297 | GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS - A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing. | 07-31-2014 |
20140219813 | GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE - A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion. The turbulence promoter is absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion | 08-07-2014 |
20140271101 | MODULATED TURBINE VANE COOLING - A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity. | 09-18-2014 |