Siemens Energy, Inc.

Arkansas Power Electronics International, Inc.

Siemens Aktiengesellschaft

Cree Fayetteville, Inc.

David J Mitchell

Anand A Kulkarni

Ramesh Subramanian

John Fraley

Roberto Marcelo Schupbach

Edward R Roesch

Bryon Western

Rod Waits

Alexander B Lostetter

Brice McPherson

Cora Schillig

Michael J Olejarski

Jie Yang

Christopher J Muller

Andrew Jeremiah Burns

Vinay Jonnalagadda

Sachin R Shinde

Bjoern Karlsson

Paul John Zombo

James P Williams

Nancy H Ulerich

Roberto M Schupbach

Derek A Bird

Rebecca L Kendall

Bulent Acar

Sankar Nellian

Cora Hitchman

Roberto Schupbach

John R Fraley

Brice R Mcpherson

Bryon P Western

A gas turbine engine seal assembly () including: a rigid seal () cooperatively configured with a structure () of a gas turbine engine to define a leakage path () including a flow-controlling section (); and a compliant seal () positioned in the leakage path.

Seal assembly in a gas turbine engine

A sealing band arrangement for a gas turbine including first and second adjoining rotor disks each including a disk arm having a slot. The sealing band arrangement includes at least one first seal strip segment located within the slots, wherein the seal strip segment includes first and second ends. The sealing band arrangement also includes a tab section that extends from the first end in order to form an underlap seal with an adjacent second seal strip segment. The underlap seal enables a thickness of the first and second ends to be substantially equivalent to a thickness of the first seal strip segment in order to improve wear life of the seal strip segment. The sealing band arrangement further includes at least one wide portion formed in the first seal strip segment wherein the wide portion is wider than a remaining portion of the first seal strip segment.

Gas turbine sealing band arrangement having an underlap seal

A turbine is provided comprising a plurality of stages, each stage comprising a rotatable disk and blades carried thereby, at least one pair of adjacent rotatable disks defining an annular gap therebetween and having respective opposing sealing band receiving slots aligned with the annular gap A sealing band is located in the opposing receiving slots to seal the annular gap Disk engagement structure is defined in the pair of adjacent rotatable disks. A clip member is coupled to the sealing band and engaged with the pair of adjacent rotatable disks through the disk engagement structure The clip member may have an aperture extending only partially through the clip member for alignment with a hole in the sealing band for engagement with a tool To improve weld geometry, the clip member may have angled surfaces and notched areas, and the sealing band may have chamfered edges.

Gas turbine including sealing band and anti-rotation device

A self-powered sensing and transmitting circuit () including a power element () and a sensing element () that is powered by the power element for generating a sensor signal responsive to a local operating environment The circuit also includes a transmitting element () powered by the power element for transmitting an output signal responsive to the sensor signal to a receiving location () remote from the circuit The power element, sensing element and transmitting element of the circuit are arranged in a generally planar and non-integrated circuit configuration formed on a substrate () component exposed to operating temperatures at or exceeding 650&#xb0; C.

Self-powered sensing and transmitting device and method of fabricating the same

A turbine including a plurality of stages, each stage including a rotatable disk and blades carried thereby. An annular gap defined between a pair of adjacent rotatable disks. A sealing band is located in opposing sealing band receiving slots formed in the adjacent disks to seal the annular gap, the sealing band including band engagement structure. A disk engagement structure is defined in the pair of adjacent rotatable disks. The disk engagement structure extends axially into the pair of adjacent rotatable disks and circumferentially aligns with the band engagement structure. A clip member is positioned in engagement with the sealing band through the band engagement structure and in engagement with the pair of adjacent rotatable disks through the disk engagement structure. The clip member restricts movement of the sealing band in only a circumferential direction of the slots.

Gas turbine including bellyband seal anti-rotation device

A method and apparatus for improved turbine bellyband rotor seal machining, installation and life are disclosed. A fixture is provided which can be temporarily attached to the turbine disks in a position straddling the gap between the disks, without destacking the turbine rotor. The fixture accepts power tools including a drill and a mill, and positions the power tools to drill and grind a rectangular slot into the disks, where the slot has the exact size and shape needed to receive an anti-rotation block which is integral to the replacement bellyband. Measuring tools are also provided which enable precise location of each of the four slots which must be machined in the disks. The resulting slots have a uniform size and shape, and are equally spaced around the circumference of the disk, thereby facilitating installation of the service bellyband from four identical segments.

Method and apparatus for improved turbine bellyband rotor seal machining, installation and life

An inductance-stable ultra high temperature circuit coupling transformer () used to transmit and receive alternating current power and/or data signals (&#x2033;). Primary (&#x2033;) and secondary (&#x2033;) windings are formed on nanostructured laminated (') primary and secondary steel cores (&#x2033;) having a Curie temperature exceeding an ultra high operating temperature. The operating range can extend from ambient to 250&#xb0; C. or to in excess of 550&#xb0; C. or up to 700&#xb0; C. with a change in inductance of less than 10% in various embodiments.

Gas turbine engine comprising an ultra high temperature circuit coupling open core transformer

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 voltage regulator circuitry () adapted to operate in a high-temperature environment of a turbine engine is provided. The voltage regulator may include a constant current source () including a first semiconductor switch () and a first resistor () connected between a gate terminal (G) and a source terminal (S) of the first semiconductor switch. A second resistor () is connected to the gate terminal of the first semiconductor switch () and to an electrical ground (). The constant current source is coupled to generate a voltage reference across the second resistorA source follower output stagemay include a second semiconductor switch () and a third resistor () connected between the electrical ground and a source terminal of the second semiconductor switch. The generated voltage reference is applied to a gating terminal of the second semiconductor switch ().

Voltage regulator circuitry operable in a high temperature environment of a turbine engine

A circuitry adapted to operate in a high-temperature environment of a turbine engine is provided. A relatively high-gain differential amplifier () may have an input terminal coupled to receive a voltage indicative of a sensed parameter of a component () of the turbine engine. A hybrid load circuitry may be coupled to the differential amplifier. A voltage regulator circuitry () may be coupled to power the differential amplifier. The differential amplifier, the hybrid load circuitry and the voltage regulator circuitry may each be disposed in the high-temperature environment of the turbine engine.

Electronic circuitry for high-temperature environments

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 ().

A circuitry () adapted to operate in a high-temperature environment of a turbine engine is provided. The circuitry may include a differential amplifier () having an input terminal () coupled to a sensing element to receive a voltage indicative of a sensed parameter. A hybrid load circuitry () may be AC-coupled to the differential amplifier. The hybrid load circuitry may include a resistor-capacitor circuit () arranged to provide a path to an AC signal component with respect to the drain terminal of the switch (e.g.,) of a differential pair of semiconductor switches, which receives the voltage indicative of the sensed parameter.

Hybrid load differential amplifier operable in a high temperature environment of a turbine engine

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

Chopper circuitry may be adapted to operate in a high-temperature environment of a turbine. A first semiconductor switch () may have a first terminal coupled to receive a first output signal from a first leg () of a differential amplifier (). A second switch () may have a first terminal coupled thru a first resistive element (R) to a second terminal of the first semiconductor switch. The first terminal of the second semiconductor switch may be coupled to receive thru a second resistive element (R) a second output signal from a second leg () of the amplifier. Switches () may be responsive to a switching control signal to respective gate terminals of the switches to supply an output signal, which alternates in correspondence with a frequency of the switching control signal from a first amplitude level to a second amplitude level, which effectively provides a doubling amplification factor.

Chopper circuitry operable in a high temperature environment of a turbine engine

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.

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Oviedo, FL, United States of America

David J Mitchell