Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Siemens Westinghouse Power Corporation

Siemens Aktiengesellschaft

Siemens Power Generation, Inc.

Christopher W Ross

Karsten Kolk

Kevin Kampka

Peter Kury

Yulia Bagaeva

Peter Schröder

Kevin Michael Light

Harald Hoell

Ching-Pang Lee

Robert John Nelson

Kok-Mun Tham

David Allen Little

Reinhard Schilp

Raul Ricardo Rico

Vyacheslav Veitsman

Lon W Montgomery

Dirk Springborn

Mirko Milazar

Sin Chien Siw

Kai Kadau

James R Pipkin

Christian Amann

Sachin R Shinde

Daniel Hofsommer

Phillip W Gravett

Keith B McLaurin

Richard B Chianese

Chirag B Patel

Keith A Miller

Patrick M Pilapil

Roger Matthews

Santiago R Salazar

Andreas Föhrigen

Bulent Acar

Jörg Richter

Andreas Andreas

Ekkehard Maldfeld

Ivan Lbov

Alexander Romanov

Rene Mahnke

James J Krizek

Joana Verheyen

Bern Luneburg

Javan Albright

Eric E Donahoo

James McCoy

Andrew Waddell

Santosh Narasimhachary

Andrew R Waddell

A rotor of a gas turbine having two adjacent rotor discs, on each of which moving blades are fastened, an annular rotor component being arranged between the rotor discs and having at its opposite ends circumferential annular grooves, in each of which a circumferential fastening projection on the respective rotor disc engages. When the rotor is stationary a first outer flank of the first annular groove rests under pressure against a first outer flank of the first fastening projection and there is play between a first inner flank of the first annular groove and a first inner flank of the first fastening projection.

Rotor comprising a rotor component arranged between two rotor discs

A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to an aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from the blade root for cooling the turbine blade.

Cover plate with flow inducer and method for cooling turbine blades

A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.

Rotor comprising a rotor component arranged between two rotor disks

A sealing element and a rotor of a gas turbine having at least one rotor disc and having an annular rotor component arranged adjacently to the rotor disc and having a plurality of sealing elements arranged distributed around the circumference. The sealing elements are fastened to the rotor disc at least in the axial direction. An inner edge portion of each of the sealing elements is adjacent to a sealing portion of the rotor component. In order to provide a seal between the sealing element and rotor component whilst at the same time enabling a relative axial displacement, a ring seal is arranged in a receiving space formed by the sealing element and rotor component.

Rotor with sealing element and ring seal

A sealing band arrangement for a gas turbine including first and second adjoining rotor disks separated by a gap wherein the first rotor disk includes an aperture. The sealing band arrangement includes at least one seal strip segment located within the gap, wherein the seal strip segment includes a first mating surface. The sealing band arrangement further includes a block having a locking section located within the aperture to stop circumferential movement of the seal strip segment relative to the first and second disks. A tapered pin element extends through the seal strip segment and the block. The tapered pin element is friction welded to both the seal strip segment and the block to attach the block to the first mating surface of the seal strip segment.

Gas turbine rotor sealing band arrangement having a friction welded pin element

A method for analyzing a three-dimensional stress concentrating feature of a component (), such as a borehole (), using a two-dimensional probabilistic technique. A circumferentially-dependent stress concentration profile around the stress concentrating feature is determined, and then a probability of failure of the component is calculated using a 2D probabilistic failure analysis of the stress concentration profile. The probabilistic failure analysis may include a Monte Carlo theta integration approach.

Method for analysis of 3D features using a 2D probabilistic analysis

A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk A non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk A compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk.

Thermal shields for gas turbine rotor

A midframe portion () of a gas turbine engine () is presented and includes a compressor section with a last stage blade to orient an air flow () at a first angle (). The midframe portion () further includes a turbine section with a first stage blade to receive the air flow () oriented at a second angle (). The midframe portion () further includes a manifold () to directly couple the air flow () from the compressor section to a combustor head () upstream of the turbine section. The combustor head () introduces an offset angle in the air flow () from the first angle () to the second angle () to discharge the air flow () from the combustor head () at the second angle (). While introducing the offset angle, the combustor head () at least maintains or augments the first angle ().

Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine

A compressor bleed cooling fluid feed system for a turbine engine for directing cooling fluids from a compressor to a turbine airfoil cooling system to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The compressor bleed cooling fluid feed system may enable cooling fluids to be exhausted from a compressor exhaust plenum through a downstream compressor bleed collection chamber and into the turbine airfoil cooling system. As such, the suction created in the compressor exhaust plenum mitigates boundary layer growth along the inner surface while providing flow of cooling fluids to the turbine airfoils.

Compressor bleed cooling fluid feed system

The compressor blade root heating system may be formed from one or more induction heaters formed from one or more induction coils positioned in close proximity to a root of a compressor blade. In one embodiment, the induction heater may be coupled to a static casing component positioned immediately upstream of a first row of compressor blades on a rotor assembly such that the induction heater is stationary during turbine engine operation. The induction heater causes eddy current formation, which heats the row one compressor blades. This heating increases the fracture toughness of the material forming the rotor and compressor blades, thereby increasing the mechanical life cycle.

Compressor blade root heating system

An oil lift pocket for a bearing surface having a plurality of channels in communication with a supply port. The plurality of channels may be formed in a substantially bow shaped configuration. Each channel may extend from a supply port and terminate at an end and away from the supply port. The oil lift pocket greatly reduces friction in slow turning operations and reduces babbitt delamination, dead zones, and nonuniform support and lift as well.

Bearing oil lift pocket

A method and apparatus for tuning the torsional natural frequency of a rotor is disclosed. At least one tuning slot is formed within the winding slots defined by radially projecting winding teeth. The tuning slot extends radially inward from the bottom of the winding slot a distance to tune the rotor to a desired torsional natural frequency. This tuning slot can be positioned preferably at the quadrature axis.

Method and apparatus to tune rotor's torsional natural frequency by geometry of rotor winding slot

An industrial coupling ( ) and associated methods are provided which are adapted to be positioned to connect a first shaft ( ) of a portion ( ) of an industrial system ( ) to a second shaft ( ) of a portion ( ) of an industrial system ( ) so that an industrial member ( ) having an opening formed therein and having a preselected opening diameter can be readily positioned over the coupling ( ). The industrial coupling ( ) preferably has a first coupler portion ( ) mounted to and integrally formed with the first shaft ( ) and having a first diameter less than the preselected opening diameter of the industrial member ( ) so that the industrial member ( ) can readily be positioned over the first coupler portion ( ) and onto the first shaft ( ). The industrial coupler ( ) preferably also has a second coupler portion ( ) adapted to be mounted on the first coupler portion ( ) and having a second diameter greater than the preselected opening diameter of the industrial member ( ) when mounted on the first coupler portion ( ) so that the industrial member ( ) after being positioned onto the first shaft ( ) cannot be readily positioned over the coupling ( ).

Shrunk on industrial coupling without keys for industrial system and associated methods

An apparatus and method for protecting synchronous generators against off-nominal frequency deviation and alternating forces excitation is provided. Particular application can be found with generators within a power generator plant integrated into a power transmission grid system. A electrical relay system is in operative association with an electrical signal representative of an actual frequency at which the generator is operating and to an electrical signal representative of an actual forcing amount at which the generator is operating. The relay system is adapted to respond to the actual frequency signal and the actual forcing signal such that the relay system compares the actual frequency signal with a predetermined desired frequency range and compares the actual forcing signal with at least one predetermined forcing amount, and selectively alarms the unit operator or trips the generator to an off-line mode depending upon the comparisons.

Apparatus and method for protecting synchronous generators against off-nominal frequency deviation and alternating forces excitation

A power generation system ( ) including an interchangeability component connecting device is provided. The system preferably includes an outer housing ( ), an inner housing ( ), a power generator ( ), interchangeable main and neutral leads ( ), main side ( ) and neutral side ( ) current transformers assembled on the respective main and neutral leads, and lead connector interfaces ( ) having a plurality of lead connectors ( ) are provided. The lead subassemblies ( ) preferably include lead subassembly platforms ( ) having main leads ( ) with main side current transformers ( ) and neutral leads ( ) with neutral side ( ) current transformers positioned thereon The main ( ) and neutral ( ) leads are interchangeably connected to first ( ) and second ( ) side portions of the power generator ( ). The present invention also provides methods of interchangeably installing main ( ) and neutral ( ) leads to first ( ) and second ( ) side portions of the power generator ( ). The present invention further provides methods of installing the main leads ( ) in a second configuration such that with no change to the power generator ( ), the phase sequence delivered at the power connections will be reversed as compared to a first configuration.

Power generation system interchangeability device and related methods

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Oviedo, FL, United States of America

Christopher W Ross