Siemens Energy, Inc.

Siemens Aktiengesellschaft

Arkansas Power Electronics International, Inc.

Siemens Power Generation, Inc.

Siemens Energy Global Gmbh & Co. Kg

Cree Fayetteville, Inc.

Anand A Kulkarni

Ramesh Subramanian

David J Mitchell

Edward R Roesch

Allister William James

Rod Waits

John Fraley

Ahmed Kamel

Alexander B Lostetter

Roberto Marcelo Schupbach

Brice McPherson

Douglas J Arrell

Bryon Western

Dustin C Boudin

Clifford Hatcher

Werner Stamm

Andrew Jeremiah Burns

Jonathan E Shipper

Kevin Licata

Christian X Campbell

Stephen M Sabol

Cora Schillig

Arindam Dasgupta

Kazim Ozbaysal

Stefan Lampenscherf

Vinay Jonnalagadda

Sachin R Shinde

Bjoern Karlsson

Kyle I Stoodt

Gerald Joseph Bruck

Gary Brian Merrill

Amit Chakraborty

David B Allen

Charalambos Polyzopoulos

James P Williams

Daniel M Eshak

James F Landy

Brian J Wessell

David Letter

Zafir A M Abdo

Thomas F Quinn

Paul J Gear

Alejandro Bancalari

Biswadip Dey

Jonathan E Shipper, Jr

Diego L Caso, Jr

Kevin C Sheehan

Sankar Nellian

Arun Meenakshinatha Iyer

Bulent Acar

Atin Sharma

Phillip Behling

Navin J Manjooran

Anita Marie Hunt

Ashkan Naeini

Christian X Campbell, Jr

Christian Xavier Campbell

Clifford Hatcher Jr

Roberto Schupbach

John R Fraley

Jr Jonathan E Shipper

Brice R Mcpherson

Bryon P Western

Roberto M Schupbach

A method of forming a component includes mixing a powdered base material and a binder to define a mixture, forming the mixture into a desired shape without melting the base material, removing the binder from the desired shape to define a skeleton, the volume of the skeleton being between 80 percent and 95 percent base material, and infiltrating the skeleton with a melting point depressant material to define a finished component, the finished component having less than one percent porosity by volume.

System and method for repairing high-temperature gas turbine components

A blade for a gas turbine includes a removed portion space, and further includes an airfoil portion defining the removed portion space, the airfoil portion formed from a base material, and a replacement component formed to fill the removed portion space. The replacement component is formed from a material that includes 50%-80% base material, 0%-30% braze material, and 0%-8% aluminum. A braze joint is formed between the airfoil portion and the replacement component to attach the replacement component to the airfoil portion and fill the removed portion space.

System and method for repairing high-temperature gas turbine blades

A support housing for use in distributing fuel in a gas turbine engine includes a main body defining an inlet aperture, a plurality of outlet apertures, and a substantially planar mounting surface. A first fuel channel has a wall that defines a first flow space and a support member extends across the first flow space and has a long axis oriented at an oblique angle with respect to the mounting surface.

Hybrid manufacturing of a support housing

A method of additive manufacturing a component. The method includes selecting powder characterization, depositing powder materials, inspecting the powder materials, selecting process and laser parameters for laser processing, laser processing the powder materials, performing layer cleanup, determining stress state and relieving, additionally inspecting the laser processed powder materials, and repeating steps until a buildup of the component is complete.

Method of additive manufacturing of components

A computer-implemented method for assessing material microstructure of a machine component involves obtaining a raw image of a section of the component captured via a microscope. The method further includes pre-processing the raw image to generate a ternary image defined by pixel data including three levels of intensities. The method further includes identifying, from the ternary image, phase boundaries delineating at a phase in a primary constituent material of the component. The method further includes determining a volume associated with the phase based on the identified phase boundaries. The proposed method may be utilized, for example, as an automated tool for assessing material degradation and for quality control of gas turbine engine components.

System and method for automated microstructure analysis

A turbine blade includes a platform with an internal cavity formed therein and an airfoil extending radially from the platform. The turbine blade includes a first portion made from ceramic matrix composite materials and a second portion made from superalloy materials. The first and second portions are selectively connected to each other via a spur and include an internal cooling circuit extending across both the first and second portions for circulating coolant therethrough. At least one supply passage extends between the internal cooling circuit and the internal platform cavity and includes an array of pin fins and turbulators for diverting coolant to the internal platform cavity.

Metal trailing edge for laminated CMC turbine vanes and blades

Materials and a process for forming a protective oxide coating. The high temperature coating system () includes at least a thermal barrier coating layer () and a thermally stable, deposit resistant protective layer () on the thermal barrier coating layer ().

Thermal barrier coating system compatible with overlay

A turbine blade having an airfoil portion includes a first ceramic matrix composite (CMC) component having a first outer surface and a second ceramic matrix composite (CMC) component having a second outer surface. The second CMC component is positioned adjacent the first CMC component such that the first outer surface and the second outer surface align with one another and at least partially define the airfoil portion. A ceramic bead is at least partially formed at an interface between the first CMC component and the second CMC component. The formation of the bead melts a portion of the first CMC component and the second CMC component, such that the ceramic bead, the first CMC component, and the second CMC component become a single contiguous component and the bead fixedly attaches the first CMC component and the second CMC component. The bead includes a bead outer surface that extends outward beyond the first outer surface and the second outer surface and an overlayer is deposited onto the airfoil portion, the overlayer bonded to the first outer surface, the second outer surface, and the bead outer surface.

Turbine blade assembly including multiple ceramic matrix composite components

A gas turbine engine blade (), including a base portion () having a cast wall, and a tip portion () attached to the base portion and having a wall () formed by an additive manufacturing process. The tip portion wall may be formed to be solid and less than 2 mm in thickness, or it may be corrugated and be greater than 2 mm in thickness. Openings () defining the wall corrugations may be semi-circular, rectangular, trapezoidal, or elliptical in cross-sectional shape. The resulting blade has lower tip mass while retaining adequate mechanical properties. The tip portion may be formed to have a directionally solidified grain structure on a base portion having an equiaxed grain structure.

Gas turbine blade with corrugated tip wall

A non-destructive method for condition assessment of a turbine component is provided. The method includes providing a laser generating a light pulse that heats the turbine component. An infrared image is then captured of the heated turbine component. An analysis of the turbine component for a particular characteristic of the turbine component may then be done. A system for the non-destructive condition assessment of a turbine component is also provided.

Laser thermography

A blackbody material application system for a turbine. The system includes a blackbody material supply and a moveable hose connected to the blackbody material supply wherein the hose sprays blackbody material onto a selected area within the turbine. The system also includes a rotatable bracket that holds the hose, wherein rotation of the bracket moves the hose toward the selected area within the turbine to enable application of the blackbody material onto the selected area. In addition, the system includes a motor for rotating the bracket and a moveable arm that holds the bracket wherein the bracket is inserted through an opening in the turbine and movement of the arm enables positioning of the bracket and hose in relative close proximity to the selected area suitable for spraying blackbody material onto the selected area.

Blackbody material application system for a turbine

A flash thermography device for generating an infrared image of each of a plurality of rotating turbine components located inside a turbine. The device includes an infrared sensor for detecting thermal energy radiated by each component. The device also includes a borescope having a viewing end located on a longitudinal axis of the borescope. The borescope is positioned in an inspection port to locate the viewing end inside the turbine such that at least one component is within a field of view of the viewing end. In addition, the device includes a flash source that generates a plurality of light pulses corresponding to the number of components that rotate during a single rotation of the rotor, wherein the light pulses are oriented substantially transverse to the longitudinal. Thermal energy radiated from each component is transmitted through the borescope to the infrared sensor to enable generation infrared images.

Flash thermography borescope

A system for automated condition assessment of a turbine component is provided. The system includes a partially enclosed photobox and a controller. The partially enclosed photobox includes a configurable rotational table adapted to carry the turbine component, at least one wall perpendicular to and abutting a horizontal platform upon which the rotational table is carried. The photobox also includes a plurality of cameras configured to be automatically positioned at locations surrounding the turbine component and capture images of the turbine component. The controller communicates with each of the cameras to respectively control the positioning of each camera in order to capture a desired view of the turbine component. At least one of the cameras is an infrared camera configured to perform flash thermography capturing a thermographic image of a portion of the turbine component. The thermographic image is used to assess the condition of the turbine component.

Flash thermography photobox

A flash thermography device for generating an infrared image of a turbine component located inside a turbine, wherein the turbine includes at least one inspection port. The device includes a flash source that generates a light pulse that heats the turbine component and an infrared sensor for detecting thermal energy radiated by the turbine component. The device also includes a borescope having a sensor end, a viewing end that includes the flash source and an interior hollow that extends between the sensor and viewing ends. The borescope is positioned in the inspection port such that the viewing end is located inside the turbine. Thermal energy radiated from the turbine component is transmitted through the hollow to the infrared sensor to enable generation of the infrared image. The device further includes a reflector located on the viewing end that directs the light pulse toward the turbine component and a flash power supply for energizing the flash source.

System to prognose gas turbine remaining useful life

A flash thermography device for generating an infrared image of a turbine component located inside a turbine. The device includes a flash enclosure having an aperture. A flash source is located in the aperture wherein the flash source generates a light pulse that heats the turbine component. The device also includes an infrared sensor for detecting thermal energy radiated by the turbine component wherein the radiated thermal energy is transmitted through the aperture to the infrared sensor to enable generation of an infrared image of the turbine component.

Flash thermography device for inspecting turbine components

Growing community of inventors

Oviedo, FL, United States of America

Anand A Kulkarni