Radially Sliding Patents (Class 415/136)
  • Patent number: 10738791
    Abstract: In one embodiment, a compressor clearance control system is provided. The compressor clearance control system includes a cooling air source, a compressor casing, and a cooling air flowpath defined through the compressor casing. The flowpath includes an inlet configured to receive cooling air from the cooling air source and an outlet configured to exhaust the cooling air to the cooling air source such that the flowpath defines a closed loop within the compressor.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Thomas Ory Moniz, Joseph George Rose
  • Patent number: 10690007
    Abstract: A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and also a ring support structure having two annular flanges, each ring sector having two tabs held respectively between the two annular flanges of the ring support structure. The two annular flanges of the ring support structure exert stress on the tabs of the ring sectors. One of the flanges of the ring support structure is elastically deformable in the axial direction of the turbine ring. The turbine ring assembly further includes a plurality of pegs engaged both in the annular flanges of the ring support structure and in the tabs of the ring sectors facing the annular flanges.
    Type: Grant
    Filed: May 12, 2016
    Date of Patent: June 23, 2020
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Lucien Henri Jacques Quennehen, Sebastien Serge Francis Congratel
  • Patent number: 10677080
    Abstract: A seal system for a moving blade system of a gas turbine includes a seal carrier including a ring section extending in the axial direction and the circumferential direction, on which a radially inner seal element is situated. A first flange section and a second flange section extend outwardly from the ring section in the circumferential direction and the radial direction and are situated at a distance from each other in the axial direction. An inner shroud section of at least one guide blade or of at least one guide blade segment includes a sealing section extending inwardly in the radial direction and in the circumferential direction, the sealing section being accommodated between the first flange section and the second flange section of the seal carrier and being connected thereto. A disk-like first seal is situated upstream from the first flange section with respect to the main flow direction of a working medium and partially abuts the first flange section radially inwardly.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: June 9, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Hermann Klingels
  • Patent number: 10677081
    Abstract: There is disclosed an axial flow machine (10) comprising an annular flow path (23); a stator ring (38) comprising a plurality of stators mounted at their radially outer ends and extending into the annular flow path (23); a non-rotating body (24) axially adjacent the stator ring (38); and an annular shroud (42) disposed between the radially inner end of the stator ring (38) and the body (24). The shroud (42) is supported on the stator ring (38) and moveable relative the body (24); and the shroud (42) cooperates with the body (24) to inhibit a flow through a clearance pathway (78) therebetween.
    Type: Grant
    Filed: August 28, 2017
    Date of Patent: June 9, 2020
    Assignee: Rolls-Royce plc
    Inventors: Alan R. Jones, Gareth J. Jones, Gary Eadon
  • Patent number: 10633997
    Abstract: An inter stage seal housing for a turbine engine having upper and lower half inter stage seal housings in which a contact sealing surface of the seal housing is restored after an interval of engine operation. The contact sealing surface is restored by fitting a replaceable wear strip on the downstream sealing surface of the seal housing. In order to fit the replaceable wear strip, a circumferential groove is machined along an outer peripheral edge of the seal housing. The groove is machined to include axial location and radial retention such that the wear strips can be slid into the upper half and lower half inter stage seal housing circumferentially from the horizontal joint. The groove includes through holes and the wear strips include corresponding threaded holes such that the wear strips can be fastened in the groove by fasteners and fastener retention hardware.
    Type: Grant
    Filed: September 16, 2013
    Date of Patent: April 28, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS AMERICAS, INC.
    Inventors: Santo F. Scimeca, Chad Garner
  • Patent number: 10526954
    Abstract: A turbocharger assembly can include a center housing; a turbine housing; and an insert disposed between the center housing and the turbine housing where a surface of the turbine housing and a first surface of the insert define a volute and where a surface of the center housing and a second surface of the insert define a chamber.
    Type: Grant
    Filed: August 6, 2015
    Date of Patent: January 7, 2020
    Assignee: Garrett Transportation I Inc.
    Inventors: Poomkuzhimannil Zachariah John, Giorgio Figura, Sunil Dayalan, Santosh V, Maltesh Kolur, Suryakant Gupta
  • Patent number: 10436046
    Abstract: A method for assembling a stator stage of a gas turbine engine and an adjustment pin to perform the assembly method to lock a vane segment in a central section of the stator stage. The method includes inserting an adjustment pin into a through hole wherein the adjustment pin includes two end sections, inserting at least one wall segment of the vane segment into a slot of a central section, rotating the adjustment pin so that the central section is correctly positioned in the stator stage, deforming a deformable part of the adjustment pin so that the now deformed part establishes a force fit with at least one segment of a corresponding structure of the central section and thereby locking the adjustment pin and thus the central section in a fixed position in the stator stage.
    Type: Grant
    Filed: May 22, 2015
    Date of Patent: October 8, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Jed Fentem, Paul Jenkinson
  • Patent number: 10385706
    Abstract: The invention relates to a rotary assembly for a turbomachine, comprising: a disk (16) having an external periphery exhibiting an alternation of slots (22) and of teeth (20), vanes (14) extending radially from the disk (16), the roots (24) of which are engaged axially and retained radially in the slots (22) of the disk, upstream and/or downstream of the disk, an annular sealing flange (52) of cavities (36) formed radially between, respectively, the roots of the vanes and the bottoms of the slots of the disk, said flange comprising an external part (56) arranged axially facing the upstream and/or downstream ends, respectively, of the teeth of the disk and of the roots of the vanes.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: August 20, 2019
    Assignee: Safran Aircraft Engines
    Inventors: St├ęphane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau
  • Patent number: 10344769
    Abstract: Aspects of the disclosure are directed to a system of an engine, comprising: a clearance control thermal ring, and a seal ring, where a radial gap with respect to an axial centerline of the engine is formed between a radial end of the clearance control thermal ring and a facing radial surface of the seal ring, where the clearance control thermal ring is made of a first material and the seal ring is made of a second material that is different from the first material, and where a first coefficient of thermal expansion of the first material is less than a second coefficient of thermal expansion of the second material.
    Type: Grant
    Filed: July 18, 2016
    Date of Patent: July 9, 2019
    Assignee: United Technologies Corporation
    Inventors: Louis R. Mouza, Philip R. Rioux
  • Patent number: 10329948
    Abstract: A pivot shaft assembly for a turbocharger with variable turbine geometry (VTG) is provided. The pivot shaft assembly may include a pivot shaft, a pivot fork extending from the pivot shaft, a VTG lever disposed on the pivot shaft, and a retention collar axially coupled to the pivot shaft such that the VTG lever is axially aligned with the retention collar and the pivot shaft.
    Type: Grant
    Filed: February 10, 2016
    Date of Patent: June 25, 2019
    Assignee: BorgWarner Inc.
    Inventors: Ryan Howell, Eli Morgan, Donald Michael Kennedy
  • Patent number: 10316677
    Abstract: A cover band assembly of a blade row of stator or rotor blades is provided. The cover band assembly comprises a blade row that is arranged inside a main flow path of a continuous-flow machine and has multiple blades which respectively have a front edge and a rear edge; and a cover band of the blade row that is at least partially embedded in a component or a component group as regarded in a longitudinal section of the continuous-flow machine, wherein a cavity is formed that surrounds the cover band and is connected to the main flow path by way of two cavity openings, wherein the front cavity opening is provided upstream of the front edge and the rear cavity opening is provided downstream of the rear edge of the blades of the blade row. Here, the cover band has a leading edge and a trailing edge.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: June 11, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KIG
    Inventor: Volker Guemmer
  • Patent number: 10280773
    Abstract: Various aspects include an alignment key for a turbomachine, along with a turbomachine including the alignment key and a related storage medium. In some cases, the alignment key includes: a body having primary axis and sized to engage a diaphragm slot in the turbomachine, the body having sidewalls extending along the primary axis; a chamfered tip section continuous with the body, the chamfered tip section sized to engage a casing slot in the turbomachine; and a slot extending through the body and the chamfered tip section, the slot having a first opening proximate an end of the body and a second opening proximate the chamfered tip section, wherein the sidewalls of the body taper from the end of the body toward the chamfered tip section.
    Type: Grant
    Filed: April 6, 2016
    Date of Patent: May 7, 2019
    Assignee: General Electric Company
    Inventors: Steven Sebastian Burdgick, Jesus Mendoza, Salvador Lopez Mata
  • Patent number: 10240485
    Abstract: The invention relates to a turbine housing (2) for an exhaust gas turbocharger. The turbine housing (2) comprises an outer housing (3) and an inner housing (4) as well as a bearing flange (5). The outer housing (3) is joined to the bearing flange (5). The inner housing (4) comprises a first shell component (7) and a second shell component (8), wherein said first shell component and said second shell component are made of different cast steel materials and are placed side by side in a transverse plane (QE), which is oriented transversely to the longitudinal axis (LA) of the turbine housing (2), and are joined to each other. The bearing flange (5) is a one-piece part, made of uniform material, of the first shell component (7).
    Type: Grant
    Filed: November 9, 2015
    Date of Patent: March 26, 2019
    Assignee: BENTELER AUTOMOBILTECHNIK GMBH
    Inventor: Elmar Grussmann
  • Patent number: 10233770
    Abstract: A position adjustment device is provided with an eccentric pin and a push rod. The eccentric pin has a rotating shaft part, and an eccentric shaft part inserted into an end in a circumferential direction of a lower-half inside member. The push rod is inserted into the lower-half inside member from an end surface in the circumferential direction of the lower-half inside member, the push rod being able to come into contact with the eccentric shaft part within the lower-half inside member. The rotating shaft part has a columnar shape with a rotational axis line. The eccentric shaft part is formed with: a side peripheral surface that comes into contact with the inner peripheral surface of an eccentric shaft hole in the lower-half inside member into which the eccentric shaft part is inserted, and a rod contact surface that comes into contact with the push rod.
    Type: Grant
    Filed: January 21, 2015
    Date of Patent: March 19, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Hiroshi Inagaki, Akihiko Shirota
  • Patent number: 10196918
    Abstract: A blade outer air seal (BOAS) segment has a transversely concave inner diameter (ID) surface along a main body portion and extending from a first circumferential end to a second circumferential end. A first mounting ear extends outward from the main body portion and cooperates with a first end portion of the main body portion to define a first circumferentially outwardly open mounting recess. A second mounting ear extends outward from the main body portion and cooperates with a second end portion of the main body portion to define a second circumferentially outwardly open mounting recess.
    Type: Grant
    Filed: June 7, 2016
    Date of Patent: February 5, 2019
    Assignee: United Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Patent number: 10190499
    Abstract: A gas turbine engine includes a convex case section. The convex case section includes an upstream case portion having a first radius, a downstream case portion having a second radius, and an intermediate case portion between the upstream case portion and the downstream case portion. The intermediate case portion has a third radius larger than the first radius and the second radius. A tension rod extends from the upstream case portion to the downstream case portion.
    Type: Grant
    Filed: December 27, 2013
    Date of Patent: January 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Joey Wong, Zhijun Zheng
  • Patent number: 10082152
    Abstract: A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth that strategically forms an interface gap (42) therebetween, resulting in blade tip gaps that are dynamically adjusted operation.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: September 25, 2018
    Assignee: SIEMENS AKTIENGSELLSCHAFT
    Inventors: Jiping Zhang, Barton M. Pepperman
  • Patent number: 10077782
    Abstract: A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing, elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing, elements have thermal properties sufficiently different to allow relative growth and geometric properties strategically selected to strategically form an interface gap therebetween (42) resulting in blade tip gaps that are dynamically adjusted operation.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: September 18, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Jiping Zhang, Barton M. Pepperman
  • Patent number: 10030541
    Abstract: A turbine engine including a turbine shroud for positioning radially outside of blades of the turbine rotor. The turbine shroud includes a carrier, a retention assembly, and a blade track. The blade track is clamped by the retention assembly, and the retention assembly is supported by the carrier.
    Type: Grant
    Filed: July 1, 2015
    Date of Patent: July 24, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Todd Engel, Robert J. Shinavski
  • Patent number: 9784116
    Abstract: A turbine shroud assembly includes a plurality of arcuate shroud block assemblies annularly arranged to form a shroud segment. The plurality of shroud block assemblies includes a first shroud block assembly having a shroud block and a second shroud block assembly having a shroud block. The first shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the first shroud block. The second shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the second shroud block.
    Type: Grant
    Filed: January 15, 2015
    Date of Patent: October 10, 2017
    Assignee: General Electric Company
    Inventors: Matthew Troy Hafner, Victor John Morgan, Frederic Woodrow Roberts, Jr.
  • Patent number: 9650905
    Abstract: A vane cluster for a gas turbine engine includes multiple singlet vanes and a forward wear liner connecting a forward edge of each singlet vane, thereby allowing the vane cluster to be manipulated as a single component.
    Type: Grant
    Filed: August 28, 2012
    Date of Patent: May 16, 2017
    Assignee: United Technologies Corporation
    Inventors: Jonathan J. Earl, Eric A. Kuehne
  • Patent number: 9605551
    Abstract: A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine.
    Type: Grant
    Filed: October 8, 2013
    Date of Patent: March 28, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Janine Sangl, Sebastian Kaltenbach, Joachim Lorenz
  • Patent number: 9528393
    Abstract: The method for removing an inner casing from a machine such as a turbine or compressor includes providing supports between the outer casing and the inner casing of the machine, removing a top part of the outer casing, then removing a top part of the inner casing, then connecting a ring sector to a bottom part of the inner casing to replace the removed top part of the inner casing, then rotating the reciprocally connected ring sector and bottom part of the inner casing around the longitudinal axis to make the bottom part of the inner casing accessible, then removing the bottom part of the inner casing, guiding the reciprocally connected ring sector and bottom part of the inner casing during rotation, to prevent movement along the longitudinal axis.
    Type: Grant
    Filed: September 10, 2013
    Date of Patent: December 27, 2016
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Tobias Christoph Huber, Gerard Froidevaux, Daniel Seng, Karsten Schwarz
  • Patent number: 9512738
    Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.
    Type: Grant
    Filed: January 30, 2013
    Date of Patent: December 6, 2016
    Assignee: United Technologies Corporation
    Inventors: Paul K. Sanchez, Kalpendu J. Parekh, William A. Daniels, John S. Tu
  • Patent number: 9482114
    Abstract: A lining for a compressor case in use with a gas turbine engine compressor is provided. The compressor includes a compressor casing, which is generally comprised of a first and second half. Inside the casing is a plurality of vanes attached to a plurality of vane bands. The vane bands are affixed to the interior of the compressor casing. A lining, comprising a carbon fiber reinforced-type material is applied to the interior of the compressor casing over the vane bands. The lining allows a minimal clearance to be between the lining and wheel blade tips spinning within the compressor casing. The carbon fiber in the lining allows the lining to withstand a high number of temperature cycles due to the use of the compressor and the gas turbine engine.
    Type: Grant
    Filed: May 31, 2011
    Date of Patent: November 1, 2016
    Inventor: Craig Rookstool
  • Patent number: 9435226
    Abstract: A gas turbine includes ring segments and isolation rings that surround a channel for high-temperature gas W from an outer peripheral side, blade rings formed in an annular shape on the outer peripheral side of the ring segments and the isolation rings, and supporting members fitted into fitting concave portions recessed from the end faces of the blade rings in the direction of the axis and supporting the ring segments and the isolation rings. An inner wall surface of the fitting concave portion has a first inclined surface that inclines so as to narrow gradually from an opening edge of the fitting concave portion toward the inside of the blade ring in the direction of the axis, and the supporting member has a second inclined surface that inclines so as to correspond to the first inclined surface.
    Type: Grant
    Filed: June 14, 2012
    Date of Patent: September 6, 2016
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventor: Yoichi Tanaka
  • Patent number: 9334756
    Abstract: An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360┬░ in length.
    Type: Grant
    Filed: October 22, 2012
    Date of Patent: May 10, 2016
    Assignee: United Technologies Corporation
    Inventors: Mark David Ring, David Cassella, Jonathan Earl, Eric Kuehne, Charles Warner
  • Patent number: 9316117
    Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.
    Type: Grant
    Filed: January 30, 2012
    Date of Patent: April 19, 2016
    Assignee: United Technologies Corporation
    Inventors: Paul K. Sanchez, Kalpendu J. Parekh, William A. Daniels, John S. Tu
  • Patent number: 9200530
    Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. The supported structure includes a hook providing an annular recess. A support ring is received in the recess. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure.
    Type: Grant
    Filed: July 20, 2012
    Date of Patent: December 1, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 9140133
    Abstract: A disclosed vane assembly includes a vane section formed of a plurality of circumferentially spaced fixed vanes. The vanes extend radially outward from an inner platform and hooked into case. The inner platform includes a mount rail extending radially inwardly from the inner platform. An air seal is attached to the inner platform of the vane section and includes a ring extending circumferentially about the axis. The disclosed air seal includes a plurality of tabs that receive lugs disposed on the mount rail. A ring nut is secured to the air seal and engaged to the mount rail for securing the vane section to the air seal.
    Type: Grant
    Filed: August 14, 2012
    Date of Patent: September 22, 2015
    Assignee: United Technologies Corporation
    Inventors: Benjamin F. Hagan, Joseph T. Caprario
  • Patent number: 9133711
    Abstract: A steam turbine of an embodiment includes: a nozzle box having a circular ring-shaped steam passage into which steam is led from a steam inlet pipe and having, on a downstream portion of the steam passage, a plurality of first-stage nozzles in a circumferential direction; and a second-stage nozzle side structure combined with the nozzle box and having a plurality of at least second-stage nozzles in a circumferential direction. Further, in the respective nozzle box and second-stage nozzle side structure, there are provided at least a pair of abutment surfaces for sealing which are not parallel to a turbine rotor axis and abutting each other. Furthermore, a seal member is provided in a part of a gap between the nozzle box and the second-stage nozzle side structure, the gap being formed by combining the nozzle box and the second-stage nozzle side structure.
    Type: Grant
    Filed: September 13, 2011
    Date of Patent: September 15, 2015
    Assignee: KABUSHIKI KAISHA TOSHIBA
    Inventors: Yoshihiro Mizutani, Masao Yamazaki
  • Publication number: 20150098791
    Abstract: A method to design a turbine including: estimating rates of thermal radial expansion for each of a stator and a rotor corresponding to a period of operation of the turbine; estimating a clearance between the rotor and the stator based on the rates of thermal radial expansion, and determining a mass or surface area of the stator or rotor based on the clearance.
    Type: Application
    Filed: October 4, 2013
    Publication date: April 9, 2015
    Applicant: General Electric Company
    Inventors: Henry G. Ballard, JR., Douglas Frank Beadie, John David Memmer
  • Publication number: 20150071767
    Abstract: A clearance control system for a rotary machine includes an outer casing including an outer casing main portion having a first radial thickness, wherein the outer casing is configured to expand at a first time rate of thermal expansion. Also included is an inner casing disposed between the outer casing and a rotary portion, the inner casing including an inner casing main portion having a second radial thickness that is less than the first radial thickness, wherein the inner casing is configured to expand at a second time rate of thermal expansion that is greater than the first time rate of thermal expansion of the outer casing. Further included is an inner casing leg configured to separate from an outer casing leg during expansion of the inner casing and configured to engage the outer casing leg during contraction of the inner casing.
    Type: Application
    Filed: September 12, 2013
    Publication date: March 12, 2015
    Applicant: General Electric Company
    Inventors: David Martin Johnson, Radu Ioan Danescu
  • Patent number: 8920113
    Abstract: An exemplary turbomachine securing apparatus includes a coupling member that couples a first component to a second component within a turbomachine. The first component and the second component are both non-rotating components during operation of the turbomachine. The coupling member limiting relative circumferential movement between the first component and the second component, and permitting relative radial movement.
    Type: Grant
    Filed: November 28, 2011
    Date of Patent: December 30, 2014
    Assignee: United Technologies Corporation
    Inventor: Eric A. Hudson
  • Patent number: 8858158
    Abstract: A steam turbine 10 is comprised of a double-structured casing configured of an outer casing 21 and an inner casing 20, a turbine rotor 23 disposed through the inner casing and having a plurality of stages of moving blades 22 implanted, and a plurality of stages of stationary blades 25 disposed alternately with the moving blades 22 in the axial direction of the turbine rotor 23 in the inner casing 20. The steam turbine 10 is further provided with a discharge passage 30 which externally guides steam, which has flown in the inner casing and passed the final stage moving blades while performing expansion work, directly from the inner casing interior.
    Type: Grant
    Filed: August 6, 2009
    Date of Patent: October 14, 2014
    Assignee: Kabushiki Kaisha Toshiba
    Inventors: Kazutaka Ikeda, Katsuya Yamashita, Takao Inukai, Kazuhiro Saito, Kouichi Kitaguchi, Shogo Iwai, Shigekazu Miyashita
  • Patent number: 8770931
    Abstract: A vane structure for a gas turbine engine includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a metal alloy inner ring.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: July 8, 2014
    Assignee: United Technologies Corporation
    Inventors: Ioannis Alvanos, Gabriel L. Suciu
  • Publication number: 20140186152
    Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion.
    Type: Application
    Filed: December 27, 2012
    Publication date: July 3, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael G. McCaffrey, Brandon T. Rouse, Thomas Almy, Igor S. Garcia, John R. Farris, Mark Borja
  • Patent number: 8757964
    Abstract: A scroll structure of a rotary machine and a rotary machine is provided in which it is possible to achieve an improvement in reliability and functionality of a rotary machine such as a turbine and to achieve a reduction in size. Provided are a scroll main body that entirely covers an area surrounding an annular channel extending in a circular shape about a rotational axis in a rotating portion of a rotary machine and a cylindrical channel extending from the annular channel at the rotational axis side and extending towards the rotating portion; and a fitting portion that supports the scroll main body with respect to a support portion and a casing accommodating the scroll main body so as to enable expansion and contraction in a radial direction centered on the rotational axis, while restraining the scroll main body in the direction along the axial axis.
    Type: Grant
    Filed: March 27, 2009
    Date of Patent: June 24, 2014
    Assignees: Pebble Bed Modular Reactor (Pty) Limited, Mitsubishi Heavy Industries, Ltd.
    Inventors: Shoki Yamashita, Toshihiro Inoue
  • Patent number: 8734090
    Abstract: A rotor blade tip clearance control apparatus for a gas turbine engine includes a plurality of circumferentially distributed segments which form an annular shroud surrounding the outer tips of a row of rotor blades. A mechanical arrangement is operatively connected to the segments. Actuation of the arrangement causes the segments to move in a radial direction thereby controlling a clearance between the segments and the outer tips. A case cooling system supplies cooling air to an engine case to which the segments are mounted. The cooling air regulates thermal expansion of the case and thereby also controls the clearance between the segments and the outer tips.
    Type: Grant
    Filed: January 19, 2010
    Date of Patent: May 27, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Leo V. Lewis
  • Publication number: 20140093358
    Abstract: A connector between a first object having a first coefficient of thermal expansion and a second object having a second coefficient of thermal expansion has a slot attaching to the second object. The slot formed by an inner shell having a slot shape and a first portion that blends into an outer surface of the second object, the slot having an enclosed portion facing forward and an aft portion that is open.
    Type: Application
    Filed: December 21, 2012
    Publication date: April 3, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Hoyt Y. Chang, Shelton O. Duelm
  • Patent number: 8667773
    Abstract: A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: March 11, 2014
    Assignee: United Technologies Corporation
    Inventor: Peter D. Silkowski
  • Publication number: 20140026585
    Abstract: A means of attachment applicable to mating parts which have substantially different coefficients of thermal expansion is disclosed. The means of attachment substantially reduces the friction between the mating surfaces while still keeping the mating parts centered with respect to one another. The approach is based on radial recessed faces wherein the radial faces slide relative to each other. There may be three or more recessed/raised faces on each mating component, which when mated, maintain the alignment between the mating parts while allowing differential growth of the mating parts. This approach also the provides a much larger bearing surface for the attachment than a radial pin/slot approach, for example, and substantially eliminates areas of high stress concentration. It is thus a more robust design for components that undergo many thousands of thermal cycles.
    Type: Application
    Filed: July 24, 2013
    Publication date: January 30, 2014
    Applicant: ICR Turbine Engine Corporation
    Inventor: Matthew Stephen Baldwin
  • Patent number: 8636465
    Abstract: A thermal expansion joint apparatus includes an insert extending through respective first and second components to loosely restrain the first component between the second component and an enlarged head of the insert, thereby allowing thermal expansion of the respective first and second components relative to each other. The insert is secured to the second component by a fastener which can be removed, for example, when the insert is to be removed from the engine.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: January 28, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Patent number: 8616839
    Abstract: A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.
    Type: Grant
    Filed: June 7, 2012
    Date of Patent: December 31, 2013
    Assignee: General Electric Company
    Inventors: Henry Grady Ballard, Jr., Fred Thomas Willett, Jr.
  • Patent number: 8510945
    Abstract: A method of assembling a heat exchanger in a gas turbine engine assembly is provided. The method includes providing a structural body including a wall having an elongated slot, providing a heat exchanger operably associated with a bracket, and providing a slip joint for coupling the bracket to the structural body. The slip joint includes a standoff, an elongated member, and a biasing member disposed about the elongated member. The standoff is inserted through the wall so that the biasing member imparts a predetermined biasing force between the bracket and the structural body. The slip joint allows relative sliding movement between the bracket and the structural body when a sliding force due to thermal expansion or contraction is greater than the biasing force.
    Type: Grant
    Filed: June 30, 2010
    Date of Patent: August 20, 2013
    Assignee: Unison Industries, LLC
    Inventors: John Hand, Bernard A. Luschek, Lonnie R. Stewart, Michael J. Gilloon, Walter A. Hundley, Jr., Jerry W. Myers, Dennis A. McQueen, Michael Peoples
  • Patent number: 8511983
    Abstract: A vane for a gas turbine engine includes an airfoil portion, a platform, and a first flange. The airfoil portion has first and second ends spaced apart in a first direction, and the first end of the airfoil portion defines an unshrouded tip. The platform is integrally formed at the second end of the airfoil, and is configured to define a flowpath boundary segment. The first flange extends from the platform away from the airfoil portion. The first flange defines a first circumferential extension and an adjacent second circumferential extension, each defining forward and aft faces. The first and second circumferential extensions are offset in a second direction such that the forward face of the first circumferential extension is substantially aligned with the aft face of the second circumferential extension in the second direction.
    Type: Grant
    Filed: February 19, 2008
    Date of Patent: August 20, 2013
    Assignee: United Technologies Corporation
    Inventors: Jess A. Weinstein, Kevin C. Eckland
  • Publication number: 20130202418
    Abstract: A section of a gas turbine engine includes a case structure having a first coefficient of thermal expansion. A continuous, ring-shaped liner has a second coefficient of thermal expansion that is substantially different than the first coefficient of thermal expansion. A flexible leaf member operatively connects the liner to the case structure. The leaf member is configured to accommodate diametrical change in the liner throughout various fan section operating temperatures.
    Type: Application
    Filed: February 6, 2012
    Publication date: August 8, 2013
    Inventors: John C. Ditomasso, Thomas J. Robertson, Gregory E. Reinhardt
  • Patent number: 8475118
    Abstract: Within such machines as gas turbine engines it is desirable to provide close association between rotating assemblies and a rotor path arrangement to reduce leakage. However, such arrangements of rotor assemblies and rotor path arrangements are subject to thermal cycling and differentials between the respective parts can lead to rub associations. In order to allow closer thermal responses between the respective rotor path arrangement and rotor assembly, a flexible assembly is provided for a liner. A face surface is presented upon a backer plate or floating ring such that the thermal response can be tuned to the reciprocal similar effects under the same conditions of the rotor assembly. In such circumstances, closer gap control can be achieved. Furthermore, rather than requiring an entire integral casing to be overhauled, generally only the face surfaces and/or the flexible assembly will require remedial action.
    Type: Grant
    Filed: June 24, 2009
    Date of Patent: July 2, 2013
    Assignee: Rolls-Royce PLC
    Inventors: Thomas Gerard Mulcaire, Steven Aleksy Radomski
  • Patent number: 8434999
    Abstract: A spline seal for a hot gas path component is provided. The spline seal may include a first metal layer and a second metal layer. The first metal layer may have a first volumetric thermal expansion coefficient. The second metal layer may be disposed adjacent the first metal layer and have a second volumetric thermal expansion coefficient. The second volumetric thermal expansion coefficient may be higher than the first volumetric thermal expansion coefficient. When the spline seal is exposed to a heat source, the first and second metal layers may deform to provide a seal between the hot gas path component and an adjacent hot gas path component.
    Type: Grant
    Filed: March 25, 2010
    Date of Patent: May 7, 2013
    Assignee: General Electric Company
    Inventors: Sergio Daniel Marques Amaral, Gary Michael Itzel, Xiuzhang James Zhang
  • Patent number: 8403634
    Abstract: A retaining seal assembly for use in a gas turbine engine is provided. The retaining seal assembly comprises an outer retaining ring coupled to an aft end of a gas turbine engine combustor. A turbine nozzle is coupled to the outer retaining ring and comprises an outer band. The outer band comprises a leading edge and an opposing trailing edge that defines a slot. A retention seal comprises a first end positioned within the slot, a generally opposing second end that contacts the outer retaining ring, and a body extending between the first end and the second end. The body further comprises an insertion portion positioned within a passage formed in the outer band. The retention seal is fabricated from a resilient material and is configured to facilitate coupling the turbine nozzle to the outer retaining ring.
    Type: Grant
    Filed: August 24, 2011
    Date of Patent: March 26, 2013
    Assignee: General Electric Company
    Inventors: Brian P. Arness, John E. Greene, Sze Bun B. Chan