General Electric Company

Doosan Heavy Industries & Construction Co., Ltd

Siemens Energy Global Gmbh & Co. Kg

Doosan Enerbility Co., Ltd.

Mahmut Faruk Aksit

Abdul-Azeez Mohammed-Fakir

Ahmad Safi

Ning Fang

Srikanth Vedantam

Osman Saim Dinc

Bharat S Bagepalli

Robert Russell Mayer

Norman Arnold Turnquist

Mehmet Demiroglu

Hamid Reza Sarshar

Biao Fang

Raymond Edward Chupp

Wei-Ming Chi

Christopher Edward Wolfe

Farshad Ghasripoor

Wei Tong

Frederick George Baily

Brian Peter Arness

Mark Edward Burnett

Iain Robertson Kellock

John Ellington Greene

Richard Robert Larsen

Gayle Hobbs Goetze

Jeffrey Arthur Benoit

Ali Ihsan Yurddas

Erdem Gorgun

Sadik Hazer

Ertugrul Tolga Duran

Gerald Burt Kliman

Anthony Holmes Furman

Shorya Awtar

Imdad Imam

Roger Neal Johnson

Daniel Ross Predmore

Victor H Correia

Glenn Herbert Nichols

Thomas Raymond Farrell

James C Przytulski

Nitin Bhate

Ming Zhou

Robert H Bartley

Adam J Weaver

James William Stegmaier

Jeffrey Reid Thyssen

Mark Arne Florin

Sami Aslam

Jong Seon Kim

Wojciech Dyszkiewicz

James Bertoncello

Gilbert Joseph Dean

Kunyuan Zhou

Markus Raben

Joseph Charles Taura

David Michael Prowse

Geon Hwan Cho

Kurt Grover Brink

Carl Anthony Flecker, Iii

Serdar Taze

Richard Cohen Lykins

Leslie Boyd Bedell

James Hopkins

Steven Wayne Russell

Thomas Paul Martin

Alpcan Uckan

Yong Hyun Lim

Dan Hasnedl

Ercan Akcan

Bora Yazgan

Serhan Güler

A seal for sealing a gap in a combustion apparatus of a gas turbine between a first side and an opposite second side. The seal includes a steel strap with a flat shape and a first metal web with a flat shape attached to the steel strap on the first side and a second metal web attached to the steel strap on the second side. Thereby the seal has a seal thickness with at least the steel strap plus the first metal web plus the thickness of the second metal web, wherein the seal thickness is at most 0.2-times of width of the seal. The new seal has an Omega shape of the second metal web, which is therefore attached on both sides with a flat shaped portion to the steel strap.

Seal for combustion apparatus

A rotor, a turbine, and a gas turbine including the same are provided. The rotor includes a pair of disks rotating about an imaginary central axis and arranged parallel to each other in an axial direction, a replaceable self-locking sealing assembly interposed between the pair of disks, and a fastening section disposed on the sealing assembly to fasten the sealing assembly to the disks. The disk includes a sealing slot disposed on an opposite surface to another adjacent disk and a head slot disposed outward from the sealing slot with respect to a radial direction of the to disk. The sealing assembly includes a main body with one end inserted into the sealing slot through the head slot from an outside of the disk and a sealing head disposed on another end of the main body to be seated on an inner wall of the head slot to restrict the main body from being moved.

Rotor including replaceable self-locking sealing assembly, turbine, and gas turbine including the same

A brush seal assembly includes a brush seal, a brush support portion, and an assembly support portion. The brush seal, which has a multitude of bristles forming an angle with respect to a radial direction of a rotating body rotated inside a casing, is disposed around an outer circumferential surface of the rotating body and is oriented with respect to the body's rotating direction. The brush support portion supports the brush seal by extending toward the rotating body while contacting a low-pressure side of the brush seal. The assembly support portion supports the brush seal and the brush support portion and to receive respectively a base end of the brush seal and an axial protrusion of the brush support portion. The brush support portion contacts the brush seal along a predetermined length, which is greater than that of a line following a bristle of the brush seal.

Brush seal assembly

A brush seal assembly is operable to seal a gap between a diaphragm and a rotor of a turbine. A brush seal assembly includes: a brush configured to have one end inserted into one side of a diaphragm and the other end protruding toward a rotor; a support strip configured to support one side of the brush; and a back plate configured to support one side of the support strip.

A brush seal assembly may include a packing body that includes an insertion groove formed inward in a circumferential direction. The insertion groove may be positioned between a rotating body and a fixed body. The packing body may include insertion holes having openings disposed toward the insertion groove at different positions and in different directions. A brush seal part includes a brush and a support member that supports the brush. The brush may extend toward the rotating body when brush is disposed in the insertion groove. A thermal expansion member may adhere to a side of the support member and thermally expand in a circumferential direction of the packing body. Fixing members may be inserted into the insertion holes, respectively, from an outside of the packing body to maintain a fixed state of the brush seal part in radial and circumferential directions of the packing body.

A brush seal assembly may seal a gap between a diaphragm and a rotor of a turbine. The brush seal assembly includes a brush, one end of which is inserted in a rotor facing surface of a diaphragm while the other end thereof protrudes toward a rotor, and a support strip spaced apart from one side of the brush so that one side end portion of the support strip is fixed and the other side end portion thereof supports one side of the brush.

A brush seal assembly may include: a packing body configured to be positioned between a rotating body and a fixing body and provided with an insertion groove; a brush seal part configured to include a brush extending toward the rotating body in a state in which one end of the brush seal part is inserted into the insertion groove and a support member supporting the brush; a thermal expansion member configured to adhere to a side of the support member and be thermally expanded in a circumferential direction of the packing body; and a fixing member configured to be fitted in the insertion groove to face the thermal expansion member to simultaneously fix the brush seal part in the circumferential direction and a radial direction of the packing body.

A compliant seal assembly for a rotating machine is provided. The seal assembly includes a static member, a movable member and a biasing member. The static member is rigidly fixed to the machine at its fore and aft ends. The movable portion has a first sealing surface configured to seal against a rotating member and a rear surface, which may be exposed to a fluid pressure to urge the first sealing surface toward a sealing position with the rotating member. The static and the movable members further include sealing surfaces at their fore, aft and end faces to seal against leakage of gas between the static and the movable members. The biasing member is configured to support the movable member on the static member and to urge the movable member away from the sealing position so as to reduce force on the rotating member during contact of the rotating member with the first sealing surface of the movable member.

Compliant seal and system and method thereof

A seal assembly includes an annular hanger having a supporting ledge. An arcuate seal segment includes an outer rail mounted on the ledge and supporting an inner seal. An arcuate carrier is mounted between the hanger and the rail, and includes a piston mounted in a bore. The bore is selectively pressurized to deploy the piston between the hanger and rail for temporarily retracting the seal segment from an adjacent rotor component.

Active seal assembly

An actuated seal assembly for controlling flow in a fluid path in turbomachinery comprising a seal and a seal carrier coupled to the seal is provided. A displacement apparatus is coupled to the seal carrier for positioning the seal so as to control the flow in the fluid path. In addition, a drive system is provided for powering the displacement apparatus.

Actuated brush seal

In a gas turbine, a supplemental seal is provided between an annular axially facing sealing surface of a nozzle support ring and an annular axially opposed sealing surface formed by circumferentially adjacent nozzle segments. Each segment carries an inner rail mounting a chordal hinge seal which engages the sealing surface of the nozzle support ring. That seal is supplemented by a generally arcuate V-shaped seal between the sealing surfaces which opens radially inwardly toward a high pressure leakage path past the chordal hinge seal. The supplemental seal is initially compressed and maintained in a compressed condition during installation by application of a solder. At operating temperature, the solder melts away, releasing the supplemental seal to seal between the nozzle support ring and nozzle segments.

Supplemental seal for the chordal hinge seals in a gas turbine and methods of installation

In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner bands of the nozzle segments on a lower pressure side of the chordal hinge seals. To minimize or prevent leakage flow across the chordal hinge seals, a generally U-shaped supplemental seal having reversely folded U-shaped marginal portions is received in a cavity formed in the axially extending sealing surface of the inner rail of the nozzle segment. At operating conditions, the marginal portions seal against the base of the cavity and the annular sealing surface of the nozzle support ring to prevent leakage flow past the chordal hinge seal from entering the hot gas path. To install the supplemental seal, the seal is first compressed and maintained in a compressed state by applying one or more wraps about the supplemental seal or an epoxy to secure the seal when compressed in the cavity. At operating temperatures, the retention means releases the seal to engage marginal portions against opposite sealing surfaces of the nozzle segment and support ring.

Supplemental seal for the chordal hinge seals in a gas turbine

In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a lower pressure side of the chordal hinge seal. The supplemental seal comprises a segmented annular composite tubular woven compliant seal disposed in a cavity along a sealing surface of the inner rail of the segment. The seal bears against the annular sealing surface of the nozzle support ring, which compresses the seal. Because of the compliant nature of the seal, a supplemental seal is formed on the low pressure side of the chordal hinge seal.

A seal is provided around a shaft extending through a cavity in a hydrogen cooled generator. The seal includes a plurality of brush seal structures adapted to reduce flow to/from the cavity to a level where the risk of creating an explosive mixture of gases is minimized. In an embodiment of the invention, a series of brush seals are provided to interface with the rotary shaft so as to define a seal for minimizing the flow of hydrogen out of the cavity. In one preferred embodiment, the seal is composed of first and second brush seal assemblies, each of which is comprised of a plurality of brush seal structures. In another embodiment, spring(s) are provided to urge the brush seal structures into sealing engagement with the rotor. If deemed necessary or desirable, a vent outlet is provided in a cavity wall remote from the hydrogen atmosphere, to remove hydrogen that has leaked through the brush seals.

Ventilated trickle seal

A brush seal assembly that in an exemplary embodiment includes an elongate brush core holder, at least three elongate brush core packs bundled together side-by-side in the brush core holder forming a single assembly. Each brush core pack includes a bristle holder and a plurality of bristles coupled to the bristle holder.

Multi-core brush seal assembly for rotary machines

Growing community of inventors

Istanbul, Turkey

Mahmut Faruk Aksit