COMPONENT FOR A GAS TURBINE ENGINE WITH A FILM HOLE

A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion. 1. A component for a gas turbine engine comprising:a hot side exposed to a hot air flow;a cool side exposed to a cooling air flow;a film hole passage extending between the cool side and the hot side with an inlet on the cool side and an outlet on the hot side, the film hole passage defining a diameter, the film hole passage further defining a side diffusion portion defining a side diffusion length between a start of the side diffusion portion and the outlet, and a layback diffusion portion defining a layback length between a start of the layback diffusion portion and the outlet, wherein the side diffusion length is greater than the layback diffusion length.2. The component of wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.3. The component of wherein the side diffusion portion defines a side diffusion angle claim 1 , α claim 1 , relative to a centerline for the film hole passage claim 1 , and the side diffusion angle is less than 12.5 degrees.4. The component of wherein the layback diffusion portion defines a layback diffusion angle claim 3 , ß claim 3 , relative to a centerline for the film hole passage claim 3 , and the layback diffusion angle is less than 12 degrees.5. The component of wherein the layback diffusion length is less than 4 times the diameter.6. The component of wherein the layback diffusion length is equal to or less than zero.7. The component of wherein the layback diffusion length is less than four times the diameter and the ...

AIRFOIL WITH TIP RAIL COOLING

An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall () enclosing an interior for the airfoil at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the airfoil to cool the tip of the airfoil. 1. An airfoil for a turbine engine , the airfoil comprising:a body defining an interior, and extending axially between a leading edge and a trailing edge to define a chord-wise direction and radially between a root and a tip to define a span-wise direction, which terminates in a tip wall and a tip rail extending from the tip wall;at least one cooling passage formed in the interior;at least one cooling cavity provided within the tip rail and comprising at least one cooling conduit defining a flow path having a centerline intersecting with a first surface of the cooling cavity and fluidly coupled to the cooling passage; andat least one film-hole non-aligned in the chord-wise direction with the at least one cooling conduit having an inlet fluidly coupled to the at least one cooling cavity at a second surface opposite the first surface and an outlet provided on an exterior surface of the tip rail.2. The airfoil of wherein the at least one cooling cavity comprises multiple cooling cavities.3. The airfoil of wherein the at least one cooling conduit comprises multiple cooling conduits.4. The airfoil of wherein the at least one cooling conduit comprises a curved cooling conduit.5. The airfoil of wherein the at least one cooling conduit comprises multiple cooling conduits.6. The airfoil of wherein the at least one cooling conduit comprises multiple cooling conduits.7. The airfoil of further comprising a plurality of film-holes provided along a distal end of the tip rail.8. The airfoil of wherein the exterior surface comprises an outer wall and the outlet is fluidly ...

BLADE WITH TIP RAIL COOLING

An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

ENGINE COMPONENT WITH HOLLOW TURBULATORS

An apparatus and method for cooling an engine component, such as an airfoil, for a turbine engine including an outer wall separating a cooling fluid flow from a hot fluid flow. A cooling circuit including a cooling passage having opposing sidewalls can be provided in the engine component. At least one turbulator can be provided between the opposing sidewalls, and can include a conduit having an inlet and an outlet passing through the at least one turbulator. 1. An airfoil for a turbine engine , the airfoil comprising:an outer wall defining a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction;a cooling circuit located within the airfoil and comprising at least one cooling passage including a first sidewall and a second sidewall; andat least one turbulator provided in the at least one cooling passage extending between the first sidewall and the second sidewall; andat least one conduit having an inlet and an outlet, fluidly coupled to the cooling circuit, and at least partially passing through the at least one turbulator.2. The airfoil of wherein the at least one turbulator comprises a plurality of turbulators.3. The airfoil of wherein the at least one conduit includes a plurality of conduits passing through each of the plurality of turbulators.4. The airfoil of wherein the inlet is provided on one of an upstream surface or a downstream surface of the at least one turbulator claim 1 , or on one of the first or second sidewalls.5. The airfoil of wherein the outlet is provided on one of an upstream surface or a downstream surface of the at least one turbulator claim 1 , or on one of the first or second sidewalls.6. The airfoil of further comprising a film hole provided in the outer wall and fluidly coupled to the at least one cooling passage wherein the film hole forms the outlet.7. The airfoil of wherein the at least ...

PROTECTIVE SHIELDS FOR IMPROVED COATING OF TURBINE COMPONENT COOLING FEATURES

A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed. 1. A method of depositing a coating on a component of a turbine engine , comprising:forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component;forming a protective shield on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture;depositing the coating on an exterior surface of the turbine component, wherein the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture; andremoving at least a portion of the protective shield to provide for passage of a cooling fluid flow in the at least one cooling flow passage and wherein the cooling fluid flow exits the turbine component through the aperture.2. The method of claim 1 , wherein the protective shield is integrally formed with the inner surface of the at least one cooling flow passage via an additive manufacturing process.3. The method of claim 1 , wherein the turbine component and the protective shield are ...

COOLING ASSEMBLY FOR A TURBINE ASSEMBLY

A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber. 1. A cooling assembly comprising:a coolant chamber disposed inside an airfoil of a turbine assembly, the coolant chamber configured to direct coolant inside the airfoil of the turbine assembly, the airfoil extending between a leading edge of the airfoil and a trailing edge of the airfoil along an axial length of the airfoil;one or more inlet cooling channels fluidly coupled with the coolant chamber and configured to direct the coolant in a direction toward a trailing edge chamber of the airfoil, the trailing edge chamber fluidly coupled with at least one of the one or more inlet cooling channels, the trailing edge chamber disposed at the trailing edge of the airfoil and including an inner surface, wherein the one or more inlet cooling channels are configured to direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber; andone or more outlet cooling channels configured to direct at least a portion of the coolant in one or more directions away from the trailing edge chamber of the airfoil.2. The cooling assembly of claim 1 , wherein at least one of the one or more inlet ...

COMPONENT FOR A GAS TURBINE ENGINE WITH A FILM HOLE

A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion. 1. A component for a gas turbine engine comprising:a hot side exposed to a hot air flow;a cool side exposed to a cooling air flow;a film hole passage extending between the cool side and the hot side with an inlet on the cool side and an outlet on the hot side, the film hole passage defining a diameter, the film hole passage further defining a side diffusion portion defining a side diffusion length between a start of the side diffusion portion and the outlet, and a layback diffusion portion defining a layback length between a start of the layback diffusion portion and the outlet, wherein the side diffusion length is greater than the layback diffusion length.2. The component of wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.3. The component of wherein the side diffusion portion defines a side diffusion angle claim 1 , α claim 1 , relative to a centerline for the film hole passage claim 1 , and the side diffusion angle is less than 12.5 degrees.4. The component of wherein the layback diffusion portion defines a layback diffusion angle claim 3 , β claim 3 , relative to a centerline for the film hole passage claim 3 , and the layback diffusion angle is less than 12 degrees.5. The component of wherein the layback diffusion length is less than 4 times the diameter.6. The component of wherein the layback diffusion length is equal to or less than zero.7. The component of wherein the layback diffusion length is less than four times the diameter and the ...

ROTATING DETONATION COMBUSTION AND HEAT EXCHANGER SYSTEM

A rotating detonation combustion (RDC) system is provided. The RDC includes a first outer wall and a second outer wall each extended around a centerline axis, and a detonation chamber formed radially inward of the second outer wall. A fuel passage extended between the first outer wall and the second outer wall, the fuel passage including a first inlet opening proximate to the aft end through which a flow of fuel is received into the fuel passage. The flow of fuel is provided through the fuel passage from the aft end to the forward end of the RDC system and to the detonation chamber. 1. A rotating detonation combustion (RDC) system , the system defining an aft end at which detonation gases exit and a forward end at which a flow of oxidizer enters , the RDC system comprising:a first outer wall and a second outer wall each extended around a centerline axis;a detonation chamber formed radially inward of the second outer wall; anda fuel passage extended between the first outer wall and the second outer wall, wherein the fuel passage comprises a first inlet opening proximate to the aft end through which a flow of fuel is received into the fuel passage, and wherein the flow of fuel is provided through the fuel passage from the aft end to the forward end of the RDC system.2. The RDC system of claim 1 , wherein the first outer wall and the second outer wall together fluidly separate the flow of fuel from the detonation chamber.3. The RDC system of claim 1 , comprising:a fuel injector in fluid communication with the fuel passage, wherein at least a portion of the flow of fuel egresses from the fuel passage through the fuel injector into the detonation chamber.4. The RDC system of claim 3 , wherein the fuel injector is positioned at the forward end of the system.5. The RDC system of claim 1 , wherein the fuel passage is extended at least partially circumferentially around the centerline axis.6. The RDC system of claim 1 , wherein the fuel passage is extended helically around ...

DOUBLE IMPINGEMENT SLOT CAP ASSEMBLY

An assembly comprises a cooling chamber disposed inside an airfoil of a turbine assembly. The cooling chamber directs cooling air inside the airfoil. The assembly comprises an impingement hole fluidly coupled with the cooling chamber. The impingement hole directs at least some of the cooling air out of the cooling chamber. A double impingement slot cap assembly forms a cover over the impingement hole. The double impingement slot cap assembly directs the cooling air exiting the cooling chamber in the airfoil through the impingement hole along one or more outer surfaces of the airfoil. 1. An assembly comprising:a cooling chamber disposed inside an airfoil of a turbine assembly, the cooling chamber configured to direct cooling air inside the airfoil;an impingement hole fluidly coupled with the cooling chamber, the impingement hole configured to direct at least some of the cooling air out of the cooling chamber; anda double impingement slot cap assembly forming a cover over the impingement hole, the double impingement slot cap assembly configured to direct the cooling air exiting the cooling chamber in the airfoil through the impingement hole along one or more outer surfaces of the airfoil.2. The assembly of claim 1 , wherein the double impingement slot cap assembly is elongated along a leading edge of the airfoil.3. The assembly of claim 1 , wherein the double impingement slot cap assembly is elongated along a stagnation region of the airfoil.4. The assembly of claim 1 , wherein the double impingement slot cap assembly is separated from the airfoil by opposite slots that are elongated in directions extending along one or more of a leading edge of the airfoil or a stagnation region of the airfoil.5. The assembly of claim 4 , wherein each of the opposite slots separating the double impingement slot cap assembly from the airfoil directs at least some of the cooling air exiting the cooling chamber through the impingement hole along different exterior surfaces of the ...

ROTATING DETONATION COMBUSTOR WITH THERMAL FEATURES

A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one fluid inlet disposed in the annular tube proximate the inlet end, the fluid inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; and at least one cooling feature disposed at an underside of the inner wall or the outer wall. The cooling feature maintains a temperature of the inner wall or the outer wall within a predetermined range. 1. A combustion system comprising:an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end;at least one fluid inlet disposed in the annular tube proximate the inlet end, the at least one fluid inlet providing a conduit through which fluid flows into the annular tube;at least one outlet disposed in the annular tube proximate the outlet end; andat least one cooling feature disposed at an underside of at least one of the inner wall and the outer wall, the at least one cooling feature for maintaining a temperature of at least one of the inner wall and the outer wall within a predetermined range.2. The combustion system of claim 1 , further comprising:at least one air plenum disposed at an underside of at least one of the inner wall and the outer wall; andat least one impingement plate disposed within the at least one air plenum,wherein at least one cooling feature is disposed within the at least one impingement plate.3. The combustion system of claim 2 , the at least one impingement plate further comprising:an inner impingement plate disposed radially inward of the inner wall; andan outer impingement plate disposed radially outward of the outer wall.4. The combustion system of claim 2 , wherein the at least one impingement plate further comprises at least one cooling hole disposed therethrough.5. The ...

CERAMIC MATRIX COMPOSITE COMPONENT INCLUDING COOLING CHANNELS AND METHOD OF PRODUCING

A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features in the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet in fluid communication with a source of a cooling fluid flow. The CMC component further includes one or more bores cutting through the plurality of longitudinally extending ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite to form a cooling channel. The component may optionally include one or more film cooling throughholes cutting through the plurality of longitudinally extending ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component. 1. A ceramic matrix composite component , comprising:a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration forming a densified body;one or more elongate functional features formed therein the densified body, and in alignment with the plurality of longitudinally extending ceramic matrix composite plies, wherein each of the one or more elongate functional features includes an inlet in fluid communication with a flow of cooling fluid from a fluid source; andone or more bores cutting through the plurality of longitudinally extending ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite component.2. A ceramic matrix composite component as claimed in claim 1 , further comprising one or more film cooling throughholes cutting through the plurality of longitudinally extending ceramic matrix composite plies ...

Ceramic matrix composite component and method of producing a ceramic matrix composite component

A method of producing a ceramic matrix composite component. The method includes positioning a first plurality of ceramic matrix composite plies on top of one another, disposing a filler pack on the first plurality of ceramic matrix composite plies, and positioning a second plurality of ceramic matrix composite plies on top of the filler pack. One of the first plurality of ceramic composite plies or the second plurality of ceramic composite plies includes a bend angle, to define an interstice between the plurality of ceramic matrix composite plies with the filler pack disposed in the interstice. The filler pack includes one or more sacrificial fibers disposed therein, that subsequent to removal provide a functional feature, such as a cooling manifold in the filler pack. The method further includes forming one or more channels coupled to the one or more functional features for the flow of a cooling fluid therethrough. A ceramic matrix composite is also disclosed.

CERAMIC MATRIX COMPOSITE COMPONENT INCLUDING COUNTERFLOW CHANNELS AND METHOD OF PRODUCING

A ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration. 1. A ceramic matrix composite component , comprising:a plurality of longitudinally extending ceramic matrix composite plies forming a densified body; anda plurality of elongated functional features formed therein the densified body, wherein each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies, wherein each of the plurality of elongated functional features includes at least one of an inlet configured in cross-ply configuration and an outlet configured in cross-ply configuration, the plurality of elongated functional features configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component, wherein the plurality of functional features are configured in alternating flow configuration.2. The ceramic matrix composite component of claim 1 , wherein the plurality of elongated functional features are enclosed within the densified body.3. The ceramic matrix composite component of claim 1 , wherein the plurality of elongated functional features comprise a plurality of counterflow ...

Ceramic matrix composite component including cooling channels in multiple plies and method of producing

A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features formed in multiple fiber plies of the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet and an outlet to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The one or more elongate functional features are configured in multiple plies of the plurality of longitudinally extending ceramic matrix composite plies to form a plurality of cooling channels in multiple plies of the ceramic matrix composite component.

COOLING ASSEMBLY FOR A TURBINE ASSEMBLY

A cooling assembly comprises a cooling chamber disposed inside a turbine assembly. The cooling chamber is configured to direct cooling air inside one or more of a combustion chamber or an airfoil of the turbine assembly. An orthogonally converging diffusing (OCD) conduit is fluidly coupled with the cooling chamber. The OCD conduit is configured to direct at least some of the cooling air out of the cooling chamber outside of an exterior surface of the one or more of the combustion chamber or the airfoil. The OCD conduit is elongated along and encompasses an intersection between a constricting plane and a diffusing plane that are traverse to each other. The OCD conduit has an interior surface with a first distance between opposing first portions of the interior surface. The first distance increases in the diffusing plane at increasing distances along the intersection from the cooling chamber toward the exterior surface. The interior surface of the OCD conduit has a second distance between opposing second portions of the interior surface of the OCD conduit. The second distance between opposing second portions decreases in the constricting plane at the increasing distances along the intersection from the cooling chamber toward the exterior surface. 1. A cooling assembly comprising:a cooling chamber disposed inside a turbine assembly, the cooling chamber configured to direct cooling air inside one or more of a combustion chamber or an airfoil of the turbine assembly;an orthogonally converging diffusing (OCD) conduit fluidly coupled with the cooling chamber, the OCD conduit configured to direct at least some of the cooling air out of the cooling chamber outside of an exterior surface of the one or more of the combustion chamber or the airfoil;wherein the OCD conduit is elongated along and encompasses an intersection between a constricting plane and a diffusing plane that are transverse to each other, the OCD conduit having an interior surface with a first distance between ...

Turbine component with rail coolant directing chamber

A turbine component includes a rail coolant directing chamber radially outward from an airfoil chamber and radially inward from a tip plate. The chamber includes an inlet fluidly coupled to the airfoil chamber to receive a coolant flow therefrom. A plurality of outlets from the rail coolant directing chamber direct the coolant flow to the at least one rail cooling passage in the rail. At least one directing wall is within the rail coolant directing chamber to direct the coolant flow towards one or more of the plurality of outlets located along at least one of the pressure side wall and an aft region of the suction side wall prior to other outlets.

METHOD OF FORMING COOLING PASSAGE FOR TURBINE COMPONENT WITH CAP ELEMENT

Methods of forming a cooling passage on a turbine component having a component wall with an internal surface and an external surface, are disclosed. An opening is formed passing through the component wall and fluidly connecting the internal and external surfaces. The opening includes a metering section extending from the internal surface to a metering end, and a diffuser area extending from the metering end to the external surface. A preformed cap element is added to close a portion of the diffuser area to form the cooling passage with a diffusion section extending from the metering end to the external surface. The preformed metal cap element includes a projection extending internally of the external surface and into the diffusion area to define an internally facing section of the diffusion section. The cooling passage extends through the component wall and fluidly connects the internal surface and the external surface. 1. A method of forming a cooling passage on a turbine component having a component wall with an internal surface and an external surface , the method comprising:forming an opening passing through the component wall and fluidly connecting the internal surface and the external surface, the opening including a metering section extending from the internal surface to a metering end, and a diffuser area extending from the metering end to the external surface; andadding a preformed metal cap element across a portion of the diffusion area of the opening to close the portion of the diffuser area to form the cooling passage with a diffusion section extending from the metering end to the external surface, the preformed metal cap element including a projection extending internally of the external surface of the component wall and into the diffusion area to define an internally facing section of the diffusion section,wherein the cooling passage extends through the component wall and fluidly connects the internal surface and the external surface.2. The method of ...

Additive supports with integral film cooling

An article of manufacture includes an article body portion (36); at least one pedestal (58A, 60A, 84, 86) integrally formed with the article body portion (36), and disposed at an outer periphery of (52), and structurally coupled to the article body portion (36); and at least one internal feature (72) disposed at least partially within the article body portion (36) and at least partially within the pedestal (58A, 60A, 84, 86). At least a portion of the internal feature (72) is hollow.

Component with mechanical locking features incorporating adaptive cooling and method of making

A hot gas path component assembly includes a first component portion that includes a first set of interlocking features and a second component portion that includes a second set of interlocking features mechanically coupled to the first set of interlocking features. A fill material is disposed at an interface between at least one surface of the first set of interlocking features and at least one surface of the second set of interlocking features. The fill material is disposed during a joining process. The second component portion is joined to the first component portion via both the fill material and the first and second sets of interlocking features.

COOLING ASSEMBLY FOR A TURBINE ASSEMBLY

A cooling assembly comprises a pin disposed inside a first chamber of an airfoil. The first chamber is disposed inside the tip end comprising a tip floor. The pin extends from a first end to a second end along a pin axis. The first end is coupled with a first surface of the first chamber and the second end is coupled with an inner floor surface of the tip floor such that the pin increases a structural load support level of the tip floor. A cooling conduit is placed inside the pin through which coolant flows. The cooling conduit is elongated along and extends around a conduit axis and is fluidly coupled with conduit channels disposed between the first and second ends of the pin. The conduit channels direct coolant out of the cooling conduit or direct coolant into the cooling conduit. 1. A cooling assembly comprising:a pin disposed inside a first chamber of an airfoil that extends from a hub end to a tip end along a radial length of the airfoil, the first chamber of the airfoil disposed inside the tip end of the airfoil, the tip end of the airfoil comprising a tip floor, the pin extending from a first end to a second end along a pin axis, the first end of the pin configured to be operably coupled with a first surface of the first chamber in the airfoil and the second end of the pin configured to be operably coupled with an inner floor surface of the tip floor such that the pin increases a structural load support level of the tip floor relative to the first end of the pin not being operably coupled with the first surface of the first chamber and the second end of the pin not being operably coupled with the inner floor surface of the tip floor; anda cooling conduit configured to be placed inside the pin through which coolant flows, the cooling conduit elongated along and extending around a conduit axis, the cooling conduit fluidly coupled with one or more conduit channels disposed between the first end of the pin and the second end of the pin, wherein the one or more ...

BLADE WITH TIP RAIL COOLING

An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade. 1. An airfoil comprising:a body defining an interior, and extending axially between a leading edge and a trailing edge to define a chord-wise direction and radially between a root and a tip to define a span-wise direction, which terminates in a tip end wall and a tip rail extending form the tip end wall;a cooling passage formed in the interior;at least two circumferentially-spaced cooling cavities within the tip rail, the at least two circumferentially-spaced cooling cavities spaced with respect to an exterior surface of the tip rail;a cooling conduit fluidly coupling the cooling passage with at least one of the at least two circumferentially-spaced cooling cavities;a connecting conduit fluidly coupling the circumferentially-spaced cooling cavities; anda film-hole having an inlet fluidly coupled to at least one of the circumferentially-spaced cooling cavities and an outlet provided on an exterior surface of the tip rail.2. The airfoil of wherein at least a portion of exterior surface of the tip rail defines a distal end of the tip rail.3. The airfoil of wherein at least another portion of the exterior surface of the tip rail defines a tip plenum and a second set of film-holes are fluidly coupled to the tip plenum.4. The airfoil of wherein the cooling conduit and the connecting conduit are angled with respect to a circumferential axis.5. The airfoil of wherein the cooling conduit and the connecting conduit comprise multiple cooling conduits and multiple connecting conduits.6. The airfoil of wherein the exterior surface of the tip rail is an outer surface of the tip rail.7. ...

IMPINGEMENT COOLED SPLINE SEAL

The present application provides a seal for use between adjacent turbine components and with a cooling flow. The seal may include an impingement baffle top plate, a base plate, and one or more spacer elements therebetween. The cooling flow provides cooling through the impingement baffle top plate. 1. A seal for use between adjacent turbine components and with a cooling flow , comprising:an impingement baffle top plate;a base plate; andone or more spacer elements therebetween;wherein the cooling flow provides cooling through the impingement baffle top plate.2. The seal of claim 1 , wherein the impingement baffle top plate comprises one or more impingement apertures therein.3. The seal of claim 1 , wherein the base plate comprises one or more base plate apertures therein.4. The seal of claim 1 , wherein the base plate comprises one or more base plate exhaust slots.5. The seal of claim 4 , wherein the one or more base plate exhaust slots comprise an exit aperture within a cavity.6. The seal of claim 1 , wherein the base plate comprises a solid structure.7. The seal of claim 1 , wherein the one or more spacer elements comprise a first spacer element positioned about a first end of the seal and a second spacer element positioned about a second end of the seal.8. The seal of claim 1 , wherein the one or more spacer elements comprise a spring element.9. The seal of claim 1 , wherein the one or more spacer elements comprise a “C” like shape.10. The seal of claim 1 , wherein the one or more spacer elements comprise a material with a different coefficient of thermal expansion than the impingement baffle top plate and/or the base plate.11. The seal of claim 1 , wherein the one or more spacer elements comprise one or more spacer element apertures.12. The seal of claim 1 , wherein the one or more spacer elements comprise a solid element.13. The seal of claim 1 , wherein the base plate and the one or more spacer elements comprise a solid element.14. The seal of claim 1 , wherein ...

TURBINE COMPONENT COOLING HOLES

A turbine component includes an internal surface, an external surface and a cooling hole. The cooling hole includes an inlet disposed on the internal surface, an outlet disposed on the external surface and a flow passage in fluid communication between the inlet and outlet. The flow passage includes a metering section extending from the inlet to a metering end, a diffusion zone extending from the metering end to the outlet, and a hooded region defined by a portion of the diffusion zone covered by a hood. The cooling hole also includes a vane extending across the flow passage, wherein a portion of the vane is disposed within the hooded region. 1. A turbine component comprising:an internal surface;an external surface; and an inlet disposed on the internal surface,', 'an outlet disposed on the external surface,', a metering section extending from the inlet to a metering end,', 'a diffusion zone extending from the metering end to the outlet, and', 'a hooded region defined by a portion of the diffusion zone covered by a hood, and, 'a flow passage in fluid communication between the inlet and outlet, the flow passage including, 'a vane extending across the flow passage, a portion of the vane disposed within the hooded region., 'a cooling hole including2. The turbine component of wherein the cooling hole comprises:a central axis extending from inlet to outlet;an upstream wall;a downstream wall disposed downstream of the upstream wall relative to a flow of mainstream gas to which the external surface is exposed;first and second opposing sidewalls interconnecting the upstream and downstream walls to define the flow passage; andthe vane extending longitudinally relative to the central axis and laterally from one of the first sidewall to the second sidewall and the upstream wall to the downstream wall.3. The turbine component of wherein the cooling hole comprises:a central axis extending from inlet to outlet;an exit plane intersecting a distal end of the hood and oriented ...

System for Rotating Detonation Combustion

Systems for rotating detonation combustion are provided herein. The system includes an inner wall and an outer wall each extended around a centerline axis, wherein a detonation chamber is defined between the inner wall and the outer wall, and an iterative structure positioned at one or both of the inner wall or the outer wall. The iterative structure includes a first threshold structure corresponding to a first pressure wave attenuation and a second threshold structure corresponding to a second pressure wave attenuation. The iterative structure provides for pressure wave strengthening along a first circumferential direction in the detonation chamber or pressure wave weakening along a second circumferential direction opposite of the first circumferential direction. The first circumferential direction corresponds to a desired direction of pressure wave propagation in the detonation chamber.

Impact cooled strip seal

Die vorliegende Anmeldung stellt eine Dichtung (100) zur Verwendung zwischen benachbarten Turbinenkomponenten (110, 120) und mit einer Kühlströmung (97) bereit. Die Dichtung (100) kann eine Pralloberplatte (220), eine Grundplatte (240) und ein oder mehrere Distanzelemente (260) dazwischen enthalten. Die Kühlströmung (97) sorgt für eine Kühlung durch die Pralloberplatte (220) hindurch. The present application provides a seal (100) for use between adjacent turbine components (110, 120) and with a cooling flow (97). The seal (100) may include an impactor plate (220), a base plate (240), and one or more spacer elements (260) therebetween. The cooling flow (97) provides cooling through the impactor plate (220).

Blade with tip rail cooling

An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

Ceramic matrix composite component including cooling channels in multiple plies and method of producing

328243-2 AB STRACT A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features formed in multiple fiber plies of the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet and an outlet to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The one or more elongate functional features are configured in multiple plies of the plurality of longitudinally extending ceramic matrix composite plies to form a plurality of cooling channels in multiple plies of the ceramic matrix composite component. Date Recue/Date Received 2020-12-09

Cooling assembly for a turbine airfoil and corresponding airfoil of a turbine assembly

An assembly comprises a cooling chamber (102) disposed inside an airfoil (100) of a turbine assembly. The cooling chamber (102) is configured to direct cooling air inside of the airfoil (100). The assembly includes an impingement hole (104) disposed inside the airfoil (100) and fluidly coupled with the cooling chamber (102). The impingement hole (104) is configured to direct at least some of the cooling air out of the cooling chamber (102). The assembly also includes a double impingement slot cap assembly (106) that is coupled with the airfoil (100). The double impingement slot cap assembly (106) forms a cover over the impingement hole (104) and is configured to direct the cooling air exiting the cooling chamber (102) in the airfoil (100) through the impingement hole (104) along one or more exterior surfaces (114, 116) of the airfoil (100).

Ceramic matrix composite component including cooling channels in multiple plies and method of producing

328243-2 AB STRACT A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features formed in multiple fiber plies of the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet and an outlet to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The one or more elongate functional features are configured in multiple plies of the plurality of longitudinally extending ceramic matrix composite plies to form a plurality of cooling channels in multiple plies of the ceramic matrix composite component. Date Recue/Date Received 2020-12-09

Cooling assembly for a turbine assembly

A cooling assembly comprises a pin disposed inside a first chamber of an airfoil. The first chamber is disposed inside the tip end comprising a tip floor. The pin extends from a first end to a second end along a pin axis. The first end is coupled with a first surface of the first chamber and the second end is coupled with an inner floor surface of the tip floor such that the pin increases a structural load support level of the tip floor. A cooling conduit is placed inside the pin through which coolant flows. The cooling conduit is elongated along and extends around a conduit axis and is fluidly coupled with conduit channels disposed between the first and second ends of the pin. The conduit channels direct coolant out of the cooling conduit or direct coolant into the cooling conduit.

Ceramic matrix composite component including cooling channels and method of producing

AB STRACT A ceramic matrix composite (CMC) component and method of fabrication including one or more elongate functional features in the CMC component. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration. Each of the one or more elongate functional features includes an inlet in fluid communication with a source of a cooling fluid flow. The CMC component further includes one or more bores cutting through the plurality of longitudinally extending ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite to form a cooling channel. The component may optionally include one or more film cooling throughholes cutting through the plurality of longitudinally extending ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component. Date Recue/Date Received 2020-12-09

Component with mechanical locking features incorporating adaptive cooling and method of making

A hot gas path component assembly includes a first component portion that includes a first set of interlocking features and a second component portion that includes a second set of interlocking features mechanically coupled to the first set of interlocking features. A fill material is disposed at an interface between at least one surface of the first set of interlocking features and at least one surface of the second set of interlocking features. The fill material is disposed during a joining process. The second component portion is joined to the first component portion via both the fill material and the first and second sets of interlocking features.

Airfoil with trailing edge cooling circuit

Airfoil for a turbine engine

Additive supports with integral film cooling

An article of manufacture includes an article body portion (36); at least one pedestal (58A, 60A, 84, 86) integrally formed with the article body portion (36), and disposed at an outer periphery of (52), and structurally coupled to the article body portion (36); and at least one internal feature (72) disposed at least partially within the article body portion (36) and at least partially within the pedestal (58A, 60A, 84, 86). At least a portion of the internal feature (72) is hollow.

Ceramic matrix composite component including cooling channels and method of producing

A ceramic matrix composite component and method of fabrication including a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration forming a densified body and one or more elongate functional features formed therein and in alignment with the plurality of longitudinally extending ceramic matrix composite plies. Each of the elongate functional features includes an inlet configured to be in fluid communication with a flow of cooling fluid from a fluid source. One or more bores cut through the plurality of ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite component. One or more film cooling throughholes cut through the ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component.

Systems for cooling a leading edge of a high speed vehicle

A leading edge assembly for a hypersonic vehicle is provided. The leading edge assembly includes an outer wall that tapers to a leading edge, the outer wall having a porous region at the leading edge; a coolant supply assembly in fluid communication with the porous region for selectively providing a flow of coolant through the porous region of the outer wall; and an insulation layer disposed between a portion of the coolant supply assembly and the outer wall, wherein the insulation layer is configured to reduce heat transfer between the coolant supply assembly and the outer wall.

Blade with tip rail cooling

An airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. The body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. The cooling passage is formed within the interior. The first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. The cooling conduit fluidly couples the cooling passage with the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.

Additive supports with integral film cooling

Additive supports with integral film cooling

An article of manufacture includes an article body portion (36); at least one pedestal (58A, 60A, 84, 86) integrally formed with the article body portion (36), and disposed at an outer periphery of (52), and structurally coupled to the article body portion (36); and at least one internal feature (72) disposed at least partially within the article body portion (36) and at least partially within the pedestal (58A, 60A, 84, 86). At least a portion of the internal feature (72) is hollow.

Turbomachine blade trailing edge cooling circuit with turn passage having set of obstructions

A turbomachine blade, and a coupon for a turbomachine blade, are disclosed. The blade may include an airfoil body having a pressure side and a suction side connected by a leading edge and a trailing edge, a coolant feed passage defined in the airfoil body, and a coolant reuse passage defined in the airfoil body. The blade may also include a first cooling circuit defined in the airfoil body. The first cooling circuit may include a rearward passage extending toward the trailing edge from and fluidly coupled to the coolant feed passage, and a radially spreading return passage extending away from the trailing edge toward and fluidly coupled to the coolant reuse passage. The cooling circuit may also include a radially extending turn passage coupling the rearward passage and the radially spreading return passage. A first set of obstructions may be positioned in the radially extending turn passage.

Cooling assembly for a turbine assembly

A cooling assembly includes a coolant chamber disposed inside an airfoil of a turbine assembly that directs coolant inside the airfoil. The airfoil extends between a leading edge and a trailing edge along an axial length of the airfoil. Inlet cooling channels are fluidly coupled with the coolant chamber and direct the coolant in a direction toward a trailing edge chamber of the airfoil. The trailing edge chamber is fluidly coupled with at least one inlet cooling channel. The trailing edge chamber is disposed at the trailing edge of the airfoil and includes an inner surface. The inlet cooling channels direct at least a portion of the coolant in a direction toward the inner surface of the trailing edge chamber. One or more outlet cooling channels direct at least a portion of the coolant in one or more directions away from the trailing edge chamber.

Airfoil with thermally conductive pins

Rotating detonation combustion and heat exchanger system

A rotating detonation combustion (RDC) system (100) is provided. The RDC includes a first outer wall (118) and a second outer wall (119) each extended around a centerline axis (117), and a detonation chamber (122) formed radially inward of the second outer wall (119). A fuel passage (105) extends between the first outer wall (118) and the second outer wall (119), the fuel passage (105) including a first inlet opening (115) proximate to the aft end (99) through which a flow of fuel (192) is received into the fuel passage (105). The flow of fuel (192) is provided through the fuel passage (105) from the aft end (99) to the forward end (98) of the RDC system (100) and to the detonation chamber (122).

Ceramic matrix composite component including counterflow channels and methods of producing

AB STRACT A ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration. Date Recue/Date Received 2020-12-09

Protective shields for improved coating of turbine component cooling features

A method of depositing a coating on a component of a turbine engine. The method includes forming a turbine component including at least one cooling flow passage in fluid communication with an aperture on a surface of the turbine component. A protective shield is formed on an inner surface of the at least one cooling flow passage and extending to an exterior of the turbine component via the aperture. During a coating process, the protective shield is configured to block the coating from being deposited in the at least one cooling flow passage via the aperture. Subsequent to coating, at least a portion of the protective shield is removed to provide for passage of a cooling fluid flow in the at least one cooling flow passage. The cooling fluid flow exits the turbine component through the aperture. A turbine component employing user of the protective shield is also disclosed.

Airfoil with thermally conductive pins

An airfoil includes a multi-part body and one or more thermally conductive pins. The multi-part body has an interior region and is formed from multiple pieces joined with each other at an interface. The pieces have multiple cavities and at least one of the pieces defines airfoil cooling channels disposed within the interior region of the body. The one or more thermally conductive pins are within the interior region of the body and extend across the interface. Each of the thermally conductive pins has a first segment disposed within a corresponding cavity of a first piece of the multiple pieces and a second segment disposed within a corresponding cavity of a second piece of the multiple pieces.

Airfoil with thermally conductive pins

An airfoil includes a multi-part body and one or more thermally conductive pins. The multi-part body has an interior region and is formed from multiple pieces joined with each other at an interface. The pieces have multiple cavities and at least one of the pieces defines airfoil cooling channels disposed within the interior region of the body. The one or more thermally conductive pins are within the interior region of the body and extend across the interface. Each of the thermally conductive pins has a first segment disposed within a corresponding cavity of a first piece of the multiple pieces and a second segment disposed within a corresponding cavity of a second piece of the multiple pieces.

Airfoil with thermally conductive pins

An airfoil includes a multi-part body and one or more thermally conductive pins. The multi-part body has an interior region and is formed from multiple pieces joined with each other at an interface. The pieces have multiple cavities and at least one of the pieces defines airfoil cooling channels disposed within the interior region of the body. The one or more thermally conductive pins are within the interior region of the body and extend across the interface. Each of the thermally conductive pins has a first segment disposed within a corresponding cavity of a first piece of the multiple pieces and a second segment disposed within a corresponding cavity of a second piece of the multiple pieces.

Component for a gas turbine engine with a film hole

A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling; hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.

Blade with tip rail cooling

An airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. The body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. The cooling passage is formed within the interior. The first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. The cooling conduit fluidly couples the cooling passage with the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.

Impingement cooled spline seal

The present application provides a seal for use between adjacent turbine components and with a cooling flow. The seal may include an impingement baffle top plate, a base plate, and one or more spacer elements therebetween. The cooling flow provides cooling through the impingement baffle top plate.