Siemens Energy, Inc.

Siemens Westinghouse Power Corporation

Siemens Aktiengesellschaft

Siemens Power Generation, Inc.

Arkansas Power Electronics International, Inc.

Other

Siemens Energy Global Gmbh & Co. Kg

Cree Fayetteville, Inc.

Ramesh Subramanian

Anand A Kulkarni

David J Mitchell

Edward R Roesch

John Fraley

Rod Waits

Alexander B Lostetter

Roberto Marcelo Schupbach

Brice McPherson

Andrew Jeremiah Burns

Bryon Western

Stephen M Sabol

David B Allen

Eckart Schumann

Cora Schillig

Ching-Pang Lee

Kok-Mun Tham

Brij B Seth

Gm Salam Azad

Vinay Jonnalagadda

Zhihong Gao

David G Sansom

Gerald Joseph Bruck

Gary Brian Merrill

Ahmed Kamel

Christian X Campbell

Paul John Zombo

Steven James Vance

Wolfram Beele

James P Williams

Silke Settegast

Nicholas F Martin, Jr

Nancy H Ulerich

Stefan Lampenscherf

Ralf Förster

Gregg P Wagner

Dimitrios Thomaidis

Roberto M Schupbach

Neil Hitchman

Axel Kaiser

Martin R Myers

Srinath Viswanathan

Michael J Warwick

Dimitrios Zois

Karren Leslie More

Chris Campbell

Bjoern Karlsson

Yongching Chen

Quingyou Han

John G Goedjen

Vasudevan Srinivasan

Sachin R Shinde

Jonathan E Shipper

Daniel Cassar

Andrea Bolz

Kelly M Sloan

Elvira Vladimirovna Anoshkina

Alexandr Sadovoy

Karsten Klein

Jonathan E Shipper, Jr

Kevin C Sheehan

Barrry L Allmon

Bulent Acar

Sankar Nellian

Lieke Wang

Michael Walker

Ashkan Naeini

Ulrich Laudien

Brig B Seth

Mercedes Keyser

Andrew Jeramiah Burns

Roberto Schupbach

John R Fraley

David Burton Allen

Elvira V Anoshkina

A hybrid three-layer system is presented. The hybrid three-layer system includes a two-layer composite system and an additively manufactured third layer comprising a lattice structure. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features. The lattice structure is in contact with a surface of the metallic substrate of the composite layer system.

High temperature capable additively manufactured turbine component design

A thermal barrier coating (TBC) with depth-varying material properties is formed on a turbine component. Exemplary depth-varying material properties include physical ductility, strength and thermal resistivity that vary from the TBC layer inner to outer surface. Exemplary ways to modify physical properties include application of plural separate overlying layers of different material composition or by varying the applied material composition during the application of the TBC layer. Various embodiment described herein also apply a calcium-magnesium-aluminum-silicon (CMAS)-retardant material over the TBC layer to retard reaction with or adhesion of CMAS containing combustion particulates to the TBC layer. In other embodiments the CMAS retardant material is also applied within engineered groove features (EGFs) that are formed in the TBC surface.

Turbine component thermal barrier coating with depth-varying material properties

Engineered groove features (EGFs) are formed within thermal barrier coatings (TBCs) of turbine engine components. The EGFs are advantageously aligned with likely stress zones within the TBC or randomly aligned in a convenient two-dimensional or polygonal planform pattern on the TBC surface and into the TBC layer. The EGFs localize thermal stress- or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. Propagation of a crack is arrested when it reaches an EGF, so that it does not cross over the groove to otherwise undamaged zones of the TBC layer. In some embodiments, the EGFs are combined with engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC.

Turbine component thermal barrier coating with crack isolating engineered groove features

Turbine and compressor casing abradable component embodiments for turbine engines vary localized porosity or abradability through use of holes or dimple depressions of desired polygonal profiles that are formed into the surface of otherwise monolithic abradable surfaces or rib structures. Abradable porosity within a rib is varied locally by changing any one or more of hole/depression depth, diameter, array pitch density, and/or volume. In various embodiments, localized porosity increases and corresponding abradability increases axially from the upstream or forward axial end of the abradable surface to the downstream or aft end of the surface. In this way, the forward axial end of the abradable surface has less porosity to counter hot working gas erosion of the surface, while the more aft portions of the abradable surface accommodate blade cutting and incursion with lower likelihood of blade tip wear.

Turbine shroud with abradable layer having ridges with holes

Methods for laser additive manufacture are disclosed in which a plurality of powder layers (and) are delivered onto a working surface (A) to form a multi-powder deposit containing at least two adjacent powders layers in contact, and then applying a first laser energy () to a first powder layer () and a second laser energy () to a second powder layer () to form a section plane of a multi-material component. The multi-powder deposit may include a flux composition that provides at least one protective feature. The shapes, intensities and trajectories of the first and second laser energies may be independently controlled such that their widths are less than or equal to widths of the first and second powder layers, their intensities are tailored to the compositions of the powder layers, and their scan paths define the final shape of the multi-material component.

Laser additive manufacture of three-dimensional components containing multiple materials formed as integrated systems

Heat insulating layered systems should have a long service life in addition to excellent heat-insulating properties. Disclosed in an inventive layered system consisting of an external ceramic layer that has a mixed crystal consisting of gadolinium zirconate and gadolinium hafnate.

Layer system comprising gadolinium solid solution pyrochlore phase

A thermal barrier coating including a two layered ceramic barrier coating, an inner ceramic layer and an outer ceramic layer, is provided. The thermal barrier coating has different thicknesses on different places of the component. In addition, the thickness of the inner ceramic layer and the thickness of the outer ceramic layer vary in relation to one another.

Ceramic thermal barrier coating system with two ceramic layers

Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section ridges that reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments at least one angularly oriented first groove formed in the ridge plateau is adapted for angular orientation upstream a turbine blade rotation direction to resist blade tip airflow leakage and the ridges are separated by second grooves that are skewed relative to the respective ridge plateaus and the substrate that are also adapted for orientation upstream the turbine blade rotation direction to resist blade tip airflow leakage.

Turbine abradable layer with asymmetric ridges or grooves

A telemetry system for use in a combustion turbine engine () having a compressor (), a combustor and a turbine () that includes a sensor () in connection with a turbine blade () or vane (). A telemetry transmitter circuit () may be affixed to the turbine blade with an electrical connecting material () for routing electronic data signals from the sensor () to the telemetry transmitter circuit, the electronic data signals indicative of a condition of the turbine blade. A resonant energy transfer system for powering the telemetry transmitter circuit may include a rotating data antenna () affixed to the turbine blade or on a same substrate as that of the circuit. A stationary data antenna () may be affixed to a stationary component such as a stator () proximate and in spaced relation to the rotating data antenna for receiving electronic data signals from the rotating data antenna.

Instrumented component for wireless telemetry

A method of forming a thermocouple (), including: depositing a first material on a component () to form a first leg (); depositing a second material through a mask () to form a pattern () on the component (), the pattern () forming a plurality of discrete second leg junction ends () and a continuous patch () of the second material comprising indiscrete lead ends of the second legs (), each second leg junction end () spanning from a respective junction () with the first leg () to the continuous patch (); and laser-ablating the continuous patch () to form discrete lead ends () of the second legs (), each lead end () electrically connected to a respective junction end (), thereby forming discrete second legs ().

Thermocouple and method of forming a thermocouple on a contoured gas turbine engine component

Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of ridges in planform patterns, establishing upper and lower wear zones. The lower wear zone reduces, redirects and/or blocks blade tip downstream airflow leakage, while the upper wear zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone. An elongated first ridge in the lower wear zone terminates in a continuous surface plateau. A plurality of second ridges or nibs, separated by grooves, project from the plateau, forming the upper wear zone. Each of the second ridges has a planform cross section smaller than the plateau planform cross section and a height smaller than the first ridge height. Some embodiments of the second ridges have spacing, planform cross sections, heights and separating groove dimensions selected for shearing when contacted by turbine blade tips.

Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface

A telemetry system for use in a combustion turbine engine () that includes a first sensor () in connection with a turbine blade () or vane (). A first telemetry transmitter circuit () is affixed to the turbine blade and routes electronic data signals, indicative of a condition of the blade, from the sensor to a rotating data antenna () that is affixed to the turbine blade or is on a same substrate as that of the circuit. A stationary data antenna () may be affixed to a stationary component () proximate and in spaced relation to the rotating data antenna for receiving electronic data signals from the rotating data antenna. A second sensor () transmits electronic data signals indicative of the stationary component to a second telemetry circuit (), which routes the signals to the stationary antenna. The stationary antenna transmits the electronic data signals to a receiver ().

An integrated, self-powered, sensing and transmitting module () that can be placed within an operating environment, such as by being affixed to a gas turbine engine component, in order to sense the local operating environment and to deliver real-time operating environment data to a location outside of the environment. Such a module may integrate a power element (); a sensing element); and a transmitting element () on a single substrate () within a single housing (). Both sensors and circuitry components are formed directly on or in the substrate in novel configurations to decrease the size and weight of the module.

Apparatus and method of monitoring operating parameters of a gas turbine

A gas turbine component () may be instrumented to provide a plurality of signals indicative of thermal measurements in a high temperature combustion environment of the gas turbine. A thermocouple arrangement may include a first thermocouple leg () disposed within a thickness of the component. At least two or more thermocouple legs () is each electrically connected to the first leg to form individual thermocouple junctions () along the first leg for conversion of respective thermal gradients to respective electrical signals, such as electromotive force (emf) based voltages. The thermocouple arrangement may be used in combination with a thermographic system () to calculate heat flux over a region of the turbine component.

Turbine component instrumented to provide thermal measurements

In a telemetry system for use in an engine, a circuit structure () affixed to a moving part () of the engine is disposed for amplifying information sensed about a condition of the part and transmitting the sensed information to a receiver external to the engine. The circuit structure is adapted for the high temperature environment of the engine and includes a differential amplifier () having an input for receiving a signal from a sensor () disposed on the part. A voltage controlled oscillator () with an input coupled to the output of the amplifier produces an oscillatory signal having a frequency representative of the sensed condition. A buffer () with an input coupled to the output of the oscillator buffers the oscillatory signal, which is then coupled to an antenna () for transmitting the information to the receiver.

Wireless telemetry electronic circuitry for measuring strain in high-temperature environments

Growing community of inventors

Oviedo, FL, United States of America

Ramesh Subramanian