Abstract: An axial flow compressor blade with a cavity formed within the blade tip region and connected by an array of holes onto the pressure side surface of the blade in the tip region so that compressed gas will flow into the cavity, and the cavity is connected by a row of tip slots arranged along the blade tip along the pressure side tip corner to discharge the compressed gas from within the cavity out onto the blade tip toward the oncoming compressed gas flow over the blade tip to reduce or eliminate any boundary layer formation and to reduce blade tip leakage flow.

Abstract: An air cooled turbine blade with a number of multiple pass serpentine flow cooling circuits extending around the airfoil surface in which a first leg of each serpentine flow circuit is located against a hot wall surface and the second legs and even the third legs of the serpentine flow circuits being located inward from the first legs. The circuits include two-pass serpentine circuits in the leading edge and trailing edge region that discharge into collection cavities, and the mid-chord section of the airfoil is cooled with three-pass serpentine circuits that discharge into long slots that open onto the blade tip.

Abstract: A turbine rotor blade with a squealer pocket formed by tip rails on the blade tip. A row of tip cooling holes extend along an inner side of the tip rails on the pressure side and the suction side to provide cooling for the blade tip and limit leakage flow across the blade tip gap. A number of vortex flow blockers are positioned within the squealer pocket and extend from the tip rails and into the squealer pocket beyond the tip cooling holes to block any formation of vortex flow from the cooling air discharged through the tip cooling holes. The tip rail crown can be narrower such that a tip crown knife edge is formed. The tip cooling holes are slanted toward the tip rails to discharge cooling air toward the blade tip gaps.

Abstract: A turbine blade of the invention includes an air foil including a plurality of cooling flow passages through which a cooling medium flows from a leading edge region to a trailing edge region, a top plate which forms the apex of the air foil, has a heat-resistant coating applied on the upper surface thereof, and includes a plurality of cooling holes, and a squealer which protrudes radially outward from the blade from the top plate, and is formed so as to extend from a leading edge end to a starting end of the trailing edge region along a suction-surface-side blade wall in a peripheral direction of the blade.

Abstract: A turbine blade includes a body having a leading edge, a trailing edge, a pressure side, a suction side, and a tip region, and a winglet arranged on the pressure side of the body in the tip region extending from a point in the tip region down stream of the leading edge to the trailing edge.

Abstract: A heat transfer apparatus, includes a member defining a wall exposed to fluid flow in a predetermined direction of flow; and a plurality of turbulators disposed on the wall. Each turbulator includes an upright front face which generally faces the direction of flow, and a back face which defines a ramp-like shape tapering from the front face to the wall.

Abstract: The invention relates to a rotor blade for a wind power plant comprising a rotor blade body, wherein the rotor blade body encloses a hollow space, wherein the rotor blade body comprises a penetration for draining the hollow space, and a functional element, wherein the functional element is displaceably connected to the rotor blade body and is disposed at the penetration. According to the invention, the functional element can be transferred from a closed position into an open position, wherein the functional element can be displaced purely by translation. Improved drainage is thereby achieved and clogging of the drain is prevented, with reduced noise production.

Abstract: A larger and highly twisted and tapered turbine rotor blade with a cooling circuit having a 3-pass horizontal flow serpentine circuit in a lower end of the airfoil, a 3-pass vertical flow serpentine circuit in the middle region of the airfoil, and a plurality of radial cooling channels in the upper end of the airfoil all connected in series to provide cooling for the airfoil.

Abstract: A turbine blade includes an airfoil, a blade tip section, a squealer tip rail, and a plurality of chordally spaced fence members. The blade tip section includes a blade tip floor located at an end of the airfoil distal from the root. The blade tip floor includes a pressure side and a suction side joined together at chordally spaced apart leading and trailing edges of the airfoil. The squealer tip rail extends radially outwardly from the blade tip floor adjacent to the suction side and extends from a first location adjacent to the airfoil trailing edge to a second location adjacent to the airfoil leading edge. The fence members are located between the airfoil leading and trailing edges and extend radially outwardly from the blade tip floor and axially from the squealer tip rail toward the pressure side.

Abstract: A turbine blade comprising a pressure wall and a suction wall joined together at leading and trailing edges and having a root portion and a blade tip region, the walls further define a hollow chamber and through which cooling air is directed in use from the root portion to the blade tip region only, characterized in that at least one of the walls defines at least one cooling rib that extends outwardly from the wall into the chamber and at least a portion of the rib tapers between the root portion and a blade tip region.

Abstract: The tip cooling arrangement of the present application reduces large cooling flow requirements which can compromise turbine performance. The tip cooling arrangement of the present application provides convective cooling of a turbine blade tip end, whether a flat tip or a squealer, by extending holes that provide fluid for film cooling the tip end. The holes are thus lengthened and extend from the relatively cooler suction side of the blade to the pressure side of the blade in close proximity to the floor of the tip end.

Abstract: 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.

Abstract: A turbine blade is provided comprising: an airfoil including an airfoil outer wall extending radially outwardly from a blade root, a squealer tip section located at an end of the airfoil distal from the root, and cooling structure. The squealer tip section comprises a blade tip surface including pressure and suction edges joined together at chordally spaced-apart leading and trailing edges of the airfoil, and a squealer tip rail. At least a substantial portion of the squealer tip rail is located near the blade tip surface suction edge. The cooling structure directs cooling fluid toward the squealer tip rail to effect impingement cooling of the rail after the cooling fluid has convectively cooled at least a portion of the airfoil outer wall. Cooling fluid is also deflected by the squealer tip rail so as to yield a very small effective flow area above the squealer tip section through which hot working gases may flow.

Abstract: A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.

Abstract: A turbine blade is provided comprising: an airfoil including an airfoil outer wall extending radially outwardly from a blade root, a squealer tip section located at an end of the airfoil distal from the root, and cooling structure. The squealer tip section comprises a blade tip surface including pressure and suction edges joined together at chordally spaced-apart leading and trailing edges of the airfoil, and a squealer tip rail. At least a substantial portion of the squealer tip rail is located near the blade tip surface suction edge. The cooling structure directs cooling fluid toward the squealer tip rail to effect impingement cooling of the rail after the cooling fluid has convectively cooled at least a portion of the airfoil outer wall. Cooling fluid is also deflected by the squealer tip rail so as to yield a very small effective flow area above the squealer tip section through which hot working gases may flow.

Abstract: A bucket for a turbine is described. The bucket includes a dovetail portion configured to couple the bucket to a turbine wheel, the dovetail portion having a lower surface. The bucket also includes a shank portion that extends from the dovetail portion and an airfoil having a root and a tip portion, an airfoil shape, and a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table I. The bucket also includes a plurality of cooling passages. The plurality includes no more than five cooling passages that extend between the root and the tip portion of the airfoil. Each of the cooling passages exits the airfoil at the tip portion, the plurality of cooling passages are positioned in a camber line pattern.

Abstract: A turbine blade for use in a gas turbine engine, the turbine blade being made from a spar and shell construction in which the spar extends from the root and forms a cavity in which cooling air is supplied to the blade. The shell is held between the tip cap and the platform in grooves. A tension rod extends from the root and through the cavity within the spar to engage with the tip cap and secure the tip cap and the shell in place. A pretension nut is secured to the tension rod on the root end and engages a surface of the root to allow for a tension to be applied to the tension rod. Ceramic rope seals are secured within the grooves between the shell ends and the groove to form a seal. An inner seal is secured within a groove of the spar and engages with a projecting member on the tip cap to form a seal. Heat shields are wrapped around the platforms to provide thermal protection to the platforms.

Abstract: A turbine blade with a stepped tip rail extending along the pressure side and the suction side of the blade tip, the stepped tip rail having tip cooling holes in the stepped portion of the tip rail to provide cooling and sealing for the blade tip. The walls of the airfoil include near wall cooling holes that open into a collector cavity formed on the backside of the tip and direct cooling air onto the backside of the tip to provide impingement cooling. The spent air from the near wall cooling holes is collected in the cavity and then discharged out the tip cooling holes. The tip cooling holes are offset inward from the near wall cooling holes to enhance the backside impingement cooling of the tip.

Abstract: An example turbine blade includes a blade having an airfoil profile extending radially toward a blade tip. A shelf is established in the blade tip. A sealing portion of the blade tip extends radially past a floor of the shelf. The sealing portion extends from a blade tip leading edge to a blade tip trailing edge. A groove is established in the blade tip. The groove extends from adjacent the shelf to adjacent the blade tip trailing edge. The groove is configured to communicate a fluid from a position adjacent the shelf to a position adjacent the blade tip trailing edge.

Abstract: A turbine rotor blade for a gas turbine engine including an airfoil and dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, the airfoil comprising: a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from a root to a tip plate; a pressure tip wall that extends radially outwardly from the tip plate, traversing from the leading edge to the trailing edge such that the pressure tip wall resides approximately adjacent to the termination of the pressure sidewall; a suction tip wall that extends radially outwardly from the tip plate, traversing from the leading edge to the trailing edge such that the suction tip wall resides approximately adjacent to the termination of the suction sidewall; and one or more tip ribs that extend substantially between the pressure tip wall and the suction tip wall.

Abstract: A turbine rotor blade with an airfoil cooling circuit and a platform cooling circuit formed integral with each other such that only one cooling flow is used. The airfoil cooling circuit includes a 5-pass aft flowing serpentine circuit with a first leg located adjacent to the leading edge region. The platform includes a mid section platform cooling circuit and an aft section platform cooling circuit. Cooling air from the second leg flows into the mid section platform cooling circuit and then into the third leg, turns at the blade tip and flows from the fourth leg into the aft section platform cooling circuit, and then into the fifth leg and up toward the blade tip. Cooling air from the fifth leg is bled off through rows of multiple impingement holes in the trailing edge and then discharged through exit holes or slots formed along the trailing edge.

Abstract: A turbine blade with a single tip rail extending along the mid-chord section of the blade tip from the trailing edge and around the leading edge region offset from the leading edge wall and ending just before the pressure side wall of the airfoil. The tip rail includes a forward side with a concave shaped cross section to form a vortex flow of cooling air on the side of the tip rail. A row of cooling holes discharge cooling air into the vortex flow formed along the concave forward side of the tip rail the tip rail also includes an aft side that is slanted downward to also form a vortex flow. The pressure side wall of the airfoil includes a concave shaped slot extending along the pressure side wall just below the tip corner, and a row of cooling holes to discharge film cooling air upward toward the tip corner.

Abstract: A turbine rotor blade with a leading edge region cooled by a series of impingement cooling cavities that repeats from near the platform to the blade tip to provide impingement cooling for the leading edge without a loss of cooling air flow volume. A cooling supply cavity delivers cooling air to a series of impingement cavities located on the pressure side, the leading edge and the suction side of the airfoil in a series flow. The spent cooling air from the series then flows up into the next series of impingement cavities to provide impingement cooling to the next section of the leading edge. The cooling air flows through multiple series of impingement cooling cavities until the blade tip, which then discharges the spent impingement cooling air through tip cooling holes.

Abstract: A rotor blade includes a bleed path opening to a suction surface, extending through the blade, exiting to at least one of the suction or a trailing surface, and through which working fluid flows under centrifugal pumping forces when the blade rotates, to passively bleed working fluid from the suction surface.

Abstract: A turbine blade with a squealer pocket formed by a tip rail extending along the pressure side and suction side of the tip. A row of diffusion notches are spaced along the inner sides of the pressure side tip rail and the suction side tip rail, each notch formed by a peak and a valley and opening into the pocket to function as a diffuser. Each notch is supplied with cooling air through a tip convective cooling hole that opens into the bottom of each notch. The pocket floor is without tip cooling holes so that the cooling air discharged into the notches function to push away the vortex flow that would form along the inner side of the tip rails to improve the cooling effectiveness and reduce the tip rail metal temperature.

Abstract: A bucket for a turbine is provided. The bucket includes an airfoil having a root portion, a tip portion, an airfoil shape, and a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table I, wherein Z is a distance from a platform on which the airfoil extends outwardly from, and X and Y are coordinates defining the profile at each distance Z from the platform. The bucket also includes a plurality of cooling passages extending between the root portion and tip portion of the airfoil, each of the plurality of cooling passages exiting at the tip portion, the plurality of cooling passages positioned in a camber line pattern.

Abstract: A turbine rotor blade with a low cooling flow serpentine circuit to provides cooling for the airfoil. The circuit includes a three pass aft flowing serpentine circuit that begins at the airfoil mid-chord region and connects to a series of multiple impingement cooling holes formed within the trailing edge region. A double pass forward flowing serpentine circuit then connects with the triple pass aft flowing serpentine circuit to provide cooling for the leading edge region and is connected to a showerhead arrangement for discharging film cooling air. A blade tip cooling channel connects with the last leg of the double pass forward flowing serpentine to form a 6-pass serpentine flow cooling circuit for the entire blade. Since only the leading edge serpentine channel discharges film cooling air, the serpentine circuit can make use of low cooling flow to provide cooling for the entire blade.

Abstract: A turbine rotor blade with a low cooling flow serpentine circuit to provides cooling for the airfoil. The circuit includes a first 3-pass serpentine flow circuit with a first leg located adjacent to the leading edge to provide impingement cooling air into a leading edge impingement cavity. The remaining cooling air flows through the first serpentine circuit to provide cooling for the blade forward mid-chord region and is discharged through film cooling holes on the pressure and suction side walls. Some of the impingement cooling air for the leading edge is discharged as film cooling air for the leading edge surface while the remaining spent cooling air flows through a blade tip channel and then into the second aft flowing 3-pass serpentine circuit to provide impingement cooling for the trailing edge region before being discharged out through exit slots and blade tip corner discharge holes.

Abstract: A turbine rotor blade with a first cooling circuit to provide cooling for the leading edge region of the airfoil and a suction side surface of the blade tip, and a second cooling circuit to provide cooling for the mid-chord region of the blade and the pressure side surface of the blade tip. The first cooling circuit includes a cooling air supply channel connected to a leading edge impingement cavity having showerhead arrangement of film cooling holes. The cooling air supply channel is connected to the suction side tip cooling channel that extends along the tip. The second cooling circuit includes a 3-pass forward flowing serpentine circuit with the third leg connected to a pressure side tip cooling channel that extends along the pressure side edge of the blade tip. Rows of tip cooling holes connect to both of the tip channels to discharge cooling air through the blade tip sections.

Abstract: A rotor blade for a wind turbine and a method for reducing rotor blade noise are disclosed. The rotor blade includes a body having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root, the surfaces further defining an interior. The rotor blade further includes at least one purge conduit defined in the tip and configured for exhausting air from the interior such that the air generally reduces noise at the tip.

Abstract: A turbine blade with a squealer pocket formed from a pressure side tip and a suction side tip rail, where two vortex cooling channels extend along the blade tip between the tip rails and an internal cooling air supply cavity to provide vortex cooling for the tip rails. Curved cooling air passages connect the cooling air supply cavity to the vortex channels and then discharge cooling air onto the pressure side wall just below the tip rail crown and into the squealer pocket from the inner surface of the suction side tip rail. Tip cooling holes are also connected to the cooling air supply cavity and discharge cooling air against the inner sides of the two tip rails to promote a vortex flow within the squealer pocket. The curved cooling holes in the vortex cooling channels are offset in order to promote the vortex flow within.

Abstract: A turbine blade with improved tip cooling includes an airfoil having a tip cap and a tip wall extending outwardly from the tip cap. A recessed portion of the tip wall forms a tip shelf. At least one tip shelf hole extends through the tip shelf in flow communication with an internal airfoil cooling circuit. At least one tip wall opening extends through the recessed portion of the tip wall radially outward of the tip shelf in flow communication with the internal cooling circuit. The recessed tip wall portion may be tapered from a wider base to a minimum thickness. In a cooling method, cooling air channeled through the tip wall openings joins and mixes with a stream of hot combustion gases downstream of where cooling air channeled through the tip shelf openings joins and mixes with the stream of hot gasses to enhance convection cooling of the blade tip.

Abstract: A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.

Abstract: A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade.

Abstract: A turbine rotor blade for use in a gas turbine engine, the rotor blade including a squealer pocket on the blade tip to provide a seal between the blade tip and the outer shroud of the engine. A row of film cooling holes extend along the pressure side wall and the suction side wall of the blade near the tip and discharge film cooling air up and over the blade tip. Associated with each of the film cooling holes is a notch formed on the edge of the tip rail in which each notch is located above a film cooling hole and functions to collect and accelerate the cooling air discharged from the film cooling hole up and into the blade tip. The notches reduce the effective thickness of the blade tip in order to reduce the heat load, and increase the effective convection surface area for the cooling air flow. The notches also function to maintain the film layer of cooling air over the blade tip longer than in the prior art without the notches.

Abstract: A turbine blade having a three pass forward flowing serpentine flow cooling circuit with a first leg connected to exit cooling holes along the trailing edge of the blade, a third and last leg discharging cooling air from the serpentine flow circuit through pressure and suction side film cooling holes, and two blade tip peripheral cooling channels extending along the pressure side and the suction side of the blade tip to provide cooling. Each peripheral channel includes film cooling holes on the blade tip side walls and exit cooling holes on the tip cap. All of the cooling air from the first leg channel that does exit out the trailing edge holes flows into the last leg without discharging through holes in the blade tip. All of the cooling air flowing out the peripheral channel cooling holes flows out from the last leg of the serpentine flow circuit.

Abstract: A rotor blade tip arrangement is provided in which winglets extend from the end of rotor blade aerofoil walls. These winglets incorporate passages which extend to coolant apertures or holes in order to present a coolant flow about the tip of the turbine rotor blade. The winglets define at least an open ended gutter channel in order to inhibit leakage flow across the tip arrangement from a pressure side P to a suction side S. The coolant flow facilitates cooling of the arrangement despite any heating caused by leakage flow across the arrangement.

Abstract: A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.

Abstract: 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.

Abstract: 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.

Abstract: A turbine blade with a tip squealer and method of rebuilding a turbine blade for a gas turbine engine. The blade is of the type including an airfoil having first and second spaced-apart sidewalls defining an interior void and joined at a leading edge and a trailing edge. The first and second sidewalls extending from a root disposed adjacent the dovetail to a tip cap for channeling combustion gases, and a squealer tip including at least one tip rib extending outwardly from the tip cap. The method includes the steps of removing the squealer tip, including the at least one rib tip, from the tip cap and adding new material to the tip cap to serve as a new squealer tip. A plurality of spaced-apart notches is formed in the new material between the leading edge and the trailing edge of the airfoil. At least one hole is formed in each notch communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.

Abstract: A method of constructing a turbine blade for a gas turbine engine is provided. The method includes casting the blade, forming a plurality of spaced-apart notches in the airfoil proximate the tip on the pressure sidewall and forming at least one hole in each tip shelf communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.

Abstract: A large tapered air cooled turbine blade having a serpentine flow cooling circuit with a first leg located adjacent to a leading edge of the blade and a third leg at the trailing edge, where the third leg includes an impingement cooling channel formed along the upper span of the blade on the trailing edge. The impingement cooling cavity includes impingement holes connected to the third leg of the serpentine flow circuit to provide cooling air into the impingement cavity, which is then discharged through exit cooling holes spaced along the upper span of the trailing edge of the blade. A separate cooling channel is formed along the lower span of the trailing edge and includes exit cooling holes to discharge cooling air through the lower span trailing edge. The upper span impingement cavity is supplied with separate cooling air from the lower span cooling cavity.

Abstract: A localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shroud.

Abstract: A turbine blade that includes a tip shroud and one or more cooling cavities formed within the tip shroud. At least one of the cooling cavities may include a plurality of ribs and a first interior wall that generally opposes a second interior wall across the cooling cavity. The ribs may be configured such that some of the ribs originate on the first interior wall of the cooling cavity and extend toward the second interior wall of the cooling cavity and some of the ribs originate on the second interior wall of the cooling cavity and extend toward the first interior wall of the cooling cavity. And, the ribs that originate on the first interior wall of the cooling cavity and the ribs that originate on the second interior wall of the cooling cavity may have an alternating arrangement.

Abstract: A turbine engine component has an airfoil portion with a pressure side and a suction side. The turbine engine component further has a first cooling microcircuit for cooling the suction side of the airfoil portion. The first cooling microcircuit is embedded within a first wall forming the suction side. The first cooling microcircuit has a circuit for allowing a cooling fluid in the first cooling microcircuit to exit at a tip of the airfoil portion. The turbine engine component also has a second cooling microcircuit embedded within a second wall forming the pressure side of the airfoil portion.

Abstract: A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section.

Abstract: A hollow turbomachine blade including an internal cooling passage, an open cavity situated at the free end of the blade and defined by an end wall and the side wall of at least one rim which extends between the leading edge and the trailing edge of the blade, and at least one cooling channel connecting said internal cooling passage to said open cavity, said cooling channel opening out at the base of the rim and the wall of the rim forming an angle relative to said end wall that is obtuse, being strictly greater than 90°. An indentation may be formed in the wall of the rim at the outlet from said cooling channel. Said blade advantageously does not include a pressure rim.

Abstract: A turbine blade (10) including an airfoil (12), the airfoil (12) including an airfoil outer wall (16) having pressure and suction sidewalls (18, 20) joined together at chordally spaced apart leading and trailing edges (22, 24) extending radially outwardly from a blade root (14) to a blade tip surface (30). A continuous squealer tip rail (40) extends radially outwardly from and substantially continuously around the blade tip surface (30) forming a radially outwardly open squealer pocket (46). The squealer tip rail (40) includes an aft portion (54) adjacent to the trailing edge (24). The aft portion (54) traverses the blade tip surface (30) between the pressure and suction sidewalls (18, 20) in a curved undulating path to define alternating forward and rearward facing pockets (56, 58, 60, 62). Each of the forward and rearward facing pockets (56, 58, 60, 62) includes a cooling hole (64a, 64b, 64c, 64d) in fluid communication with a cooling fluid circuit (49) within the airfoil (10).

Abstract: A turbine engine component has an airfoil portion having a pressure side, a suction side, a leading edge, a trailing edge, and a tip. The component further has a first cooling microcircuit embedded in a pressure side wall, a second cooling microcircuit embedded in a suction side wall, and a system for cooling the tip comprising a first tip cooling microcircuit receiving cooling fluid from the first cooling microcircuit and a second tip cooling microcircuit receiving cooling fluid from the second cooling microcircuit.