General Electric Company

Michael Joseph Danowski

Gulcharan Singh Brainch

Sean Robert Keith

Leslie Eugene Leeke, Jr

Jonathan Philip Clarke

Roger Dale Wustman

Ching-Pang Lee

Joshua Tyler Mook

Steven Robert Brassfield

John Peter Heyward

Michael G Abbott

Hardev Singh

Chad Daniel Kleinow

Jonathan Phillip Clarke

Michael George Abbott

A ceramic shroud assembly includes a tip shroud having an outer platform supporting at least one seal tooth, a shroud cap less brittle than the outer platform and including a shroud cap base on the outer platform, and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located at clockwise and counter-clockwise distal ends respectively of the base. A rotor assembly may include a circumferential row of turbine blades made of a ceramic material and extending radially outwardly from a disk of a turbine rotor. The turbine blades include airfoils having the airfoil tip shrouds and the shroud caps at blade tips. The clockwise and counter-clockwise contact surfaces of circumferentially adjacent ones of the shroud caps contact each other. The shroud and the platform may be made of a ceramic or ceramic matrix composite material and the shroud cap may be made of a metallic material.

Cap for ceramic blade tip shroud

A rotor blade assembly includes a shank, an airfoil that is formed integrally with the shank, and a removable platform coupled between said shank and said airfoil via a friction fit. A method of assembling a gas turbine engine rotor blade assembly that includes a removable platform, and a gas turbine engine rotor assembly including the removable platform are also described herein.

Turbine rotor blade and method of assembling the same

A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein.

Turbine rotor blade assembly and method of assembling the same

An airfoil for a gas turbine engine has opposed pressure and suction sidewalls extending between a leading edge and a trailing edge. The airfoil includes an array of radially-spaced apart longitudinally-extending lands which define a plurality of trailing edge slots therebetween. Each of the trailing edge slots has an inlet in fluid communication with an interior of the airfoil and an exit in fluid communication with the trailing edge. At least one of the lands is tapered such that a width of the land measured in a radial direction decreases from the suction sidewall to the pressure sidewall.

Turbine nozzle with trailing edge convection and film cooling

A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, and an airfoil, and forming a plurality of openings between the platform inner surface and the platform outer surface to facilitate cooling an exterior surface of the platform.

Method and apparatus for cooling gas turbine engine rotor blades

An airfoil core die includes a tab for forming a continuous and smooth contour and extension of a first trailing edge slot recessed all to a bottom of the airfoil. The contour is formed on each airfoil core at injection and is maintained through to finish casting of the airfoil.

Apparatus and methods for cooling slot step elimination

A method for fabricating a rotor blade includes casting the turbine rotor blade to include a shank, and a platform having an upper surface and a lower surface, and coupling a first component to the rotor blade such that a first substantially hollow plenum is defined between the first component, the shank, and the platform lower surface.

A cooled turbine element including an airfoil and a flowpath boundary member extending laterally from either an inboard end or an outboard end of the airfoil. The member has a flowpath face and an outside face which is cooler than said flowpath face creating a tendency for the member to deflect in a direction away from the flowpath face and causing a thermally induced tensile radial stress in a region of the trailing edge of the airfoil. The element has an interior cooling passage and at least one cooling hole extending from the interior cooling passage to an opening located in an area upstream from the stressed region of the trailing edge to cool the area so the airfoil thermally deflects to a shape corresponding to that of the boundary member thereby lowering the thermally induced tensile radial stress in the airfoil at the trailing edge thereof.

Method for reducing cooled turbine element stress and element made thereby

An article comprising an airfoil surface is provided with a thermal insulating outer layer on at least one region, but not all, of the airfoil surface. The region is selected from the airfoil surface which has been observed to experience more strenuous environmental operating conditions during service operation than the airfoil surface outside of the region. In one form, the thermal insulating outer layer is applied to at least one region of each of a plurality of airfoil surfaces. Each airfoil surface is disposed about an axis of rotation with the region of each airfoil surface facing generally outwardly from the axis of rotation and from each other. The airfoil surfaces are rotated about the axis of rotation while a thermal insulating material contacts at least the regions.

Partially coated airfoil and method for making

An article having a design external aerodynamic shape includes a body with a body external surface and an outer portion external surface of an outer portion bonded with a part of but less than substantially all of the body surface. The external surfaces of the body and outer portion each define less than the design external aerodynamic shape. However, together they define such shape. The article is made by selecting the design external aerodynamic shape from an existing article having a first body and a first outer portion. A replacement outer portion is selected in an amount less than the first outer portion and bonded with a region less than substantially all of a replacement body external surface. The replacement body has a replacement body external surface and replacement body external shape different from the first body substantially by that amount. The replacement body is made with the replacement body external shape. Then the replacement outer portion is bonded with the region of the replacement body external surface. The result is that the external surfaces of the replacement body and replacement outer portion together define the design external aerodynamic shape.

Aerodynamic article with partial outer portion and method for making

A turbine blade includes a platform and an airfoil having a plurality of trailing edge slots separated by land areas larger than the slots. The slots have an exit diffusion half angle of about two degrees. Cooling air flows through the slots and over a trailing edge of the airfoil. The platform includes a plurality of openings extending through the platform at an angle. The openings are positioned between a suction side of the blade and a second end of the platform. The openings transport disk post cooling air to a surface of the platform and provide cooling for the platform.

Apparatus and methods for turbine blade cooling

An airfoil core die includes a tab for forming a continuous and smooth contour and extension of a first trailing edge slot recessed wall to a bottom of the airfoil. The contour is formed on each airfoil core at injection and is maintained through to finish casting of the airfoil.

Growing community of inventors

Cincinnati, OH, United States of America

Michael Joseph Danowski