Siemens Energy, Inc.

Siemens Power Generation, Inc.

Siemens Aktiengesellschaft

Siemens Westinghouse Power Corporation

Other

Siemens Energy Global Gmbh & Co. Kg

Yevgeniy P Shteyman

Harry A Albrecht

Jay Alan Morrison

Matthew R Porter

John A Orosa

James S Marshall

John Giaimo

Daniel M Eshak

Anil L Salunkhe

Jonathan M Leagon

Lijuan Han

Matthew J Delisa, Iii

Gary Brian Merrill

Mrinal Munshi

John W Finneran

Robert Watson Spitzer

Robert Angel

Daryl J Graber

Daniel F Riveros

Jay Edgar Lane

Steven James Vance

Robert T Brooks

Daniel George Thompson

Matthias Hase

Michael Huth

Steven C Butner

Scott M Widrig

John N Strain

Drew Ehlert

Scott W Smith

Thomas Heylmun

Ching-Pang Lee

David James Wiebe

Christian X Campbell

William Richard Ryan

Thomas Barrett Jackson

Chris Campbell

Friedrich T Rogers

Brian D Nereim

Brian Harry Terpos

Phillip W Gravett

Stephen Williamson

Piyush Sane

George J Obranic, Jr

Sudeep Bosu

Keith J Gordon

Keith W Piersall

Ashley N Girdich

James Alfonso

Randy Tindell

Brian Micklos

Christopher Scogin

Frank Tsai

Michael Whitty

Jeffrey D Kesten

Cristina Cook

James Marshall

A turbine blade includes a platform, a blade airfoil attached to one side of the platform, a blade root attached to the other side of the platform, a manifold attached to the blade root. The blade root defines a first cooling passage and a second cooling passage. The manifold includes an outer wall, a first compartment having a first flow area defined by a first aperture formed at the outer wall, and a second compartment having a second flow area defined by a second aperture formed at the outer wall. The first compartment meters a non-zero first flow of cooling air to the first cooling passage through the first flow area. The second compartment meters a non-zero second flow of cooling air to the second cooling passage through the second flow area that is different than the first flow area.

Manifold for turbine blade of gas turbine engine

An air separator for a turbine engine is provided. The air separator includes an aft air separator member () having an annular frame () which defines a chamber () configured to engage disc shoulders () configured in a first stage of the turbine engine. The aft air separator member () is constrained from movement along a radial direction by the disc shoulders engaged in the chamber of the aft air separator member. A forward air separator member () is affixed at a forward end thereof to a torque tube () to constrain movement along the radial direction. The forward air separator includes at an aft end thereof a flange () that engages the aft air separator member. The forward air separator member is constrained from outward radial movement along the radial direction by way of a recess () constructed in a portion of the aft air separator member.

Air separator for a turbine engine

A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct structure is provided and includes an inlet end in fluid communication with the channel outlet and includes an outlet end in fluid communication with an area of reduced pressure relative to the air duct structure inlet end. An exit cavity is located at the air duct structure outlet end, wherein the exit cavity effects a reduced pressure at the outlet end to draw air from the cooling channel into the air duct.

Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity

A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A trailing edge full span flap is removable secured behind the trailing edge of the tangential strut in a fluid flow direction and extending between the outer cylindrical surface and the inner cylindrical surface where the full span flap minimizes vortex shedding of the fluid flow from the tangential strut.

Turbine exhaust cylinder/turbine exhaust manifold bolted full span turbine exhaust flaps

A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A first flap is arranged diagonally between the tangential strut and the outer cylindrical surface or the inner cylindrical surface where the first flap minimizes vortex shedding of the fluid flow from the tangential strut.

Turbine exhaust cylinder/ turbine exhaust manifold bolted part span turbine exhaust flaps

Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.

Turbine exhaust cylinder/ turbine exhaust manifold bolted stiffening ribs

Disclosed are a system for damping vibrations of a gas turbine exhaust and a method to damp vibrations of a gas turbine exhaust. The system includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer clamped by a plurality of studs.

Damping design to reduce vibratory response in the turbine exhaust manifold centerbody

An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling.

Gas turbine engine with multiple component exhaust diffuser operating in conjunction with an outer case ambient external cooling system

A sealing arrangement for a gas turbine including exhaust and manifold diffusers separated by a circumferential diffuser gap. The sealing arrangement includes a forward clamp arrangement attached to the exhaust diffuser wherein the forward clamp arrangement includes a forward groove. The sealing arrangement also includes an aft clamp arrangement attached to manifold diffuser wherein the aft clamp arrangement includes an aft groove. Further, the sealing arrangement includes a flexible circumferential seal including forward and aft loop portions. The forward loop portion is located in the forward groove and the aft loop portion is located in the aft groove wherein the circumferential seal extends across the circumferential diffuser gap to seal the circumferential diffuser gap. The forward and aft loop portions are moveable in the forward and aft grooves to enable movement of the circumferential seal in a circumferential direction to accommodate thermal expansion of the exhaust and manifold diffusers.

Moveable sealing arrangement for a gas turbine diffuser gap

An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Industrial gas turbine exhaust system with splined profile tail cone

Disclosed are a casing arrangement and a method to reduce critical panel mode response in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A plurality of stiffening ribs are coupled to a surface of the inner flow path which effectively increases the stiffness reducing the critical panel mode response.

Turbine exhaust cylinder / turbine exhaust manifold bolted stiffening ribs

Industrial gas turbine exhaust system diffuser inlet lip

Modular industrial gas turbine exhaust system

Industrial gas turbine exhaust system with modular struts and collars

An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The adjustable transition duct support system includes an adjustable forward transition flexible support assembly in contact with a transition duct body, whereby the forward transition flexible support assembly may be formed from a base extending toward the transition duct body and first and second side support arms extending from the base to the transition duct body. The first and second side support arms may be formed from a plurality of flex plates spaced from each other with spacers that provide rigidity in circumferential and radial directions and flexibility in an axial direction. The number of flex plates used may be varied to accommodate different turbine engines. The adjustable transition duct support system may have natural frequencies for circumferential and radial modes above two engine orders.

Transition support system for combustion transition ducts for turbine engines

Growing community of inventors

West Palm Beach, FL, United States of America

Yevgeniy P Shteyman