Abstract: A cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor, through one or more impellers, and into row one turbine vanes and one or more rows of turbine blades for increasing the cooling capacity of the turbine vanes and blades. Such a configuration increases cooling capacity, which in turn increases the capacity for growth within the turbine engine, creates a larger cooling fluid to gas side pressure differential and reduces amount of bleed off of cooling fluids from the compressor, thereby increasing efficiency of the turbine engine.

Abstract: A turbine rotor blade with a platform hot spot cooling circuit that includes a bracket occupying a space below the platform on the pressure side of the blade neck and forming a cooling air supply hole connected to the blade cooling air supply channel and opening into an impingement cavity located below a hot spot location on the pressure side platform surface. A number of film cooling holes are connected to the impingement cavity and open onto the platform surface to cool the hot spot location.

Abstract: A turbine exhaust cylinder for an industrial gas turbine engine with an external blower that delivers cooling air to an inner space of the exhaust cylinder that provides cooling for the struts that support the exhaust cylinder. The cooling air passes over the bearing housing and then up through a space formed between a fairing and the strut. The cooling air is then discharged through a cover plate.

Abstract: A turbine rotor blade for an industrial gas turbine engine with a platform cooling circuit that flows from the suction side of the platform and around both the leading edge and trailing edge of the platform, and then along the pressure side platform to cover the entire platform surface. The cooling air flows along smaller diameter cooling holes that cover substantially the entire pressure side platform surface and is then discharged out through openings onto the pressure side mate-face.

Abstract: A turbine stator vane with an endwall cooling circuit that includes a first ten-pass serpentine flow cooling circuit and a second ten-pass serpentine flow cooling circuit. Each serpentine circuit is connected to cooling air feed holes supplied from an endwall impingement cavity, where cooling air serpentines along the leading edge section of the endwall, along the two mate faces, and then serpentines along the trailing edge section where the cooling air is discharged from exit holes spaced along the trailing edge side of the endwall.

Abstract: A turbine rotor blade has a number of serpentine flow cooling circuits to provide cooling to forward and aft sections of the airfoil and to upper span and lower span sections of the airfoil in order to provide specific cooling to directed sections of the airfoil. A common cooling air supply channel extends the entire spanwise length of the airfoil and supplies cooling air to each of the serpentine flow cooling circuits.

Abstract: A stator vane for an industrial turbine, the vane includes a serpentine flow cooling circuit for cooling of the airfoil, and a separate purge air channel to supply purge air to the rim cavities. The purge channel is formed as a separate channel from the serpentine flow channels so that the purge air is not heated by the hot metal and has smooth surfaces so that pressure losses is minimal.

Abstract: A turbine rotor disk with rotor blades secured within slots, where the rotor disk includes a radial extension that occupies a space where a dead rim cavity would be formed, and in which the radial extension includes a cooling air chamber with impingement cooling air holes directed to discharge impingement cooling air to a backside surface of the platforms of the blades.

Abstract: A high temperature resistant turbine stator vane with an airfoil section made from oxide dispersion strengthened (ODS) material extruded through a die, an internal cooling circuit is machined into the airfoil section after the extrusion, and then two endwalls are formed separately and then secured to the airfoil section ends to form the stator vane. Film cooling holes can be drilled into the airfoil section and the endwalls.

Abstract: A turbine rotor blade with a root section having a cooling air feed hole opening onto a bottom surface of the root section of the blade. The feed hole includes a clam shell shape with a forward side wider than an aft side of the feed hole, and the feed hole is sloped upward from the forward side to the aft side to form a scoop so that cooling air flowing along a live rim cavity in a rotor disk will more easily flow into the feed holes with less loss of pressure.

Abstract: A turbine rotor blade with a forward flowing serpentine flow cooling circuit in the airfoil and a serpentine flow cooling circuit formed within the blade tip formed in series to provide cooling air flow through the airfoil and then through the blade tip. Cooling air from the airfoil serpentine circuit is bled off to provide cooling of the trailing edge region through T/E exit slots. The tip serpentine cooling circuit includes legs on the pressure and suction side walls with tip edge cooling holes to provide layers of film cooling air for the blade tip rails. A separate cooling air circuit is used in the leading edge region to provide convection cooling, impingement cooling and film cooling for the leading edge region.

Abstract: A turbine rotor blade with a trailing edge region cooling circuit that is formed by three rows of ribs each forming a row of metering and impingement holes followed by a series of exit slots each formed with parallel passages that form a metering section followed by a diffusion section. A forward flowing multiple pass serpentine flow cooling circuit cools the mid-chord region and supplies the cooling air for the trailing edge region circuit. A separate leading edge cooling circuit with metering and impingement cooling followed by film cooling cools the leading edge region.

Abstract: A turbine vane with a low flow near wall multiple impingement cooling circuit in which a thin thermal skin is bonded over a main support spar that together forms a series of chordwise extending collection and impingement chambers extending from the leading edge region to the trailing edge region of the airfoil. Cooling air from a cooling air supply cavity flows through feed holes and into a first one of the collection chambers located in the leading edge region, and then through impingement cooling holes for backside impingement cooling of the airfoil wall. the series of collection and impingement is repeated along the airfoil wall until the spent impingement air is discharged through exit holes on both sides of the trailing edge region.

Abstract: A turbine blade with small diffusers in the cooling channels and trip strips on the channel walls to produce a very high internal convection. A trailing edge cooling channel includes a diffuser on a lower end of the channel formed by ribs with decreasing width. A forward flowing serpentine flow cooling circuit includes a tip turn and a root turn with a small diffuser formed by the tip turn and a small diffuser formed on a lower end of the third leg of the serpentine formed by ribs with decreasing width.

Abstract: A turbine stator vane with a cooling circuit that improves the cooling effectiveness of the airfoil as well as collects any dirt particles before passing the clean cooling air through the cooling circuit. The airfoil includes a 3-pass aft flowing serpentine circuit with a first leg located along the airfoil leading edge and connected to a showerhead arrangement for film cooling discharge. A cooling air supply channel is located between the first leg and the second leg of the serpentine flow circuit, and the cooling supply channel includes ribs arranged to produce a vortex flow within the cooling air that collects the dirt particles within a center of the vortex flow and deposits the dirt particles at the bottom of the channel. The vortex flow cooling air flows through impingement holes to produce impingement cooling on the backside wall of the leading edge with clean cooling air.

Abstract: A BOAS segment for a turbine includes an impingement cavity with circular cooling air supply holes adjacent to a leading edge side of the cavity and is connected to main body axial cooling holes that open onto the trailing edge side of the BOAS segment. Cooling supply holes are located at the four corners of the impingement cavity and are connected to multiple cooling holes that open onto both edges of the segment in that corner. Thin metering cooling slots are positioned along the mate face sides in the cavity and are each connected to multiple cooling holes that discharge cooling air onto the mate face edges.

Abstract: A ring segment for a blade outer air seal which includes an array of separated floating wall surfaces each extending from a pedestal and having an inner side with a fibrous metal pad secured and a TBC secured over the pads. The pedestals are formed by diffusion chambers formed between an outer side and an inner side of the ring segment. Purge air holes connect the diffusion chambers to the impingement cavity formed above the ring segment. Thin slots form the separated floating wall surfaces and connect the diffusion chambers to discharge cooling air through the sides of the floating wall surfaces. Cooling air holes also pass through the pedestals to discharge cooling air onto the TBC surfaces.

Abstract: A film cooling hole for a turbine airfoil having a diffusion section with a convergent wall and two divergent side walls, and with a thin exit slot that opens onto the airfoil surface. The divergent side walls have an expansion of 15 to 25 degrees and the convergent wall converges up to 15 degrees. The film hole is formed by an electrode than is pushed into the metal surface to form the divergent side walls and then pivoted to form the convergent wall.

Abstract: A blade outer air seal with ring segments forming a mate face gap in which a riffle seal is placed to seal the axial gap. The riffle seal includes a horizontal plate and a vertical plate extending from a bottom surface of the horizontal plate and occupies the axial gap space. The bottom end of the vertical extending plate is angled in a direction of rotation of rotor blades and includes ribs that form open slots in the riffle seal. The ring segments include metering holes that discharge cooling air into the slots to discharge film cooling air onto the hot gas surface of the BOAS and cool the ring segments.

Abstract: A turbine vane with an airfoil extending between an inner diameter endwall and an outer diameter endwall, where thin slots are formed between the airfoil and the endwall in the trailing edge section in which cooling air is supplied to produce impingement cooling and purge air to prevent hot gas flow across the slots. The thin slot functions to thermally de-couple the thin airfoil trailing edge section from the thick endwall to prevent cracks.