Source: https://patents.justia.com/patents-by-us-classification/415/135
Timestamp: 2020-08-06 13:42:19
Document Index: 788505290

Matched Legal Cases: ['art 51', 'art 52', 'art 51', 'art 52', 'art 42', 'arts 52', 'art 42']

Resilient Patents and Patent Applications (Class 415/135) - Justia Patents Search
Justia Patents Rotary Kinetic Fluid Motors Or Pumps Patents Including Thermal Expansion Joint Patents Resilient Patents (Class 415/135)
Resilient Patents (Class 415/135)
Turbine ring assembly comprising a plurality of ring sectors made of ceramic matrix composite material
Patent number: 10718235
Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of ceramic matrix composite material, each ring sector having a portion forming an annular base with an inside face defining the inside face of the turbine ring, and an outside face from which there extends a wall defining an internal housing in which a holder member made of metal material is present, the holder member being connected to the ring support structure and including a body from which elastically deformable holder elements extend inside the internal housing on either side of the body, the holder elements bearing against the wall.
Inventors: Clément Roussille, Thierry Tesson
Patent number: 10662965
Abstract: A sealing structure includes: an insertion hole formed in a sealing plate; a sealing ring provided in the insertion hole; a first rotating body provided to the shaft, at least a part of the first rotating body positioned inside the insertion hole; a second rotating body disposed at a position apart from the compressor impeller than the first rotating body and having a maximum outer diameter larger than a minimum inner diameter of the insertion hole; and an annular receiving groove formed by the first rotating body and the second rotating body and receiving an inner circumferential surface side of the sealing ring.
Inventors: Yoshiaki Hirai, Nobuyuki Ikeya, Kouta Kimachi
Patent number: 10533437
Abstract: A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.
Inventors: Timothy Dale, Swati G. Bhanderi
Patent number: 10436045
Abstract: A support device supports an inner member of a fixed body including the inner member and an outer member, the inner member being arranged around a rotating body and divided into upper and lower sections and the outer member being arranged in at least a part around the inner member and divided into upper and lower sections.
Inventor: Shinya Honda
Compact advanced passive tip clearance control
Patent number: 10344612
Abstract: A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.
Inventors: Eric A. Hudson, Michael G. McCaffrey, Stanley J. Funk, Scott D. Virkler
Gas turbine engine with compliant layer for turbine vane assemblies
Patent number: 10273818
Abstract: A turbine vane assembly for use in a gas turbine engine includes an endwall, a flow path component, and a load-distribution system. The endwall is arranged around a central axis of the turbine vane assembly. The flow path component is configured to direct fluid flow through the turbine vane assembly. The load-distribution system is positioned between the endwall and the flow path component to distribute loads transmitted between the endwall and the flow path component.
Patent number: 10247041
Abstract: A frame employed in a turbine exhaust case of a gas turbine engine includes a frame outer ring, a frame inner ring, and a plurality of frame struts that connect the frame outer ring to the frame inner ring. The frame outer ring includes a plurality of bosses disposed circumferentially around the frame outer ring, wherein at least one of the plurality of bosses includes a mounting surface that receives and secures a removable bracket to the frame outer ring that supports a weight of the frame.
Patent number: 10214872
Abstract: The present invention provides a foundation for a wind turbine. To reduce set-up time and to allow complete alignment of the platform which carries the base flange of the tower construction, the invention provides a foundation with a cage structure having an upper stress distribution flange connected by a plurality of tensioned anchor bolts to a lower flange. The flanges are separated by a number of distance elements whereby the shape of the cage structure becomes fixed by the combination between tensioned bolts and distance elements. Since the cage structure has a fixed shape, the upper stress distribution flange can be aligned before the cage structure is embedded in concrete, and it becomes unnecessary to wait for the concrete to harden.
Patent number: 10167877
Abstract: An object of the present invention is to decrease a surging limit flow rate at a low flow rate time, by increasing the inflow velocity to the blade of the impeller wheel, by providing a resistive element that narrows in the radial direction a passage cross section of an air intake passage which communicates between a impeller wheel of a centrifugal compressor and an air intake opening. The centrifugal compressor includes: the compressor housing 9 having the air intake opening 13 opened in a rotary shaft direction, and the air intake passage 11; and the impeller wheel 7 for compressing the air flowing in from the air intake opening 13, inside the housing.
Inventors: Seiichi Ibaraki, Isao Tomita, Hiroshi Suzuki
Structural guide vane circumferential load bearing shear pin
Patent number: 10167737
Abstract: A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.
Inventors: Gregory E. Reinhardt, Paul Thomas Rembish, Steven L. Conner, Thomas B. Hyatt, Steven J. Feigleson, Carl Brian Klinetob
Patent number: 10138750
Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.
Inventors: Michael G. McCaffrey, Benjamin F. Hagan, David Richard Griffin
Patent number: 10132177
Abstract: A hollow vane, includes a main portion, of which the cavity is closed by a cover, that is produced by expanding the main portion relative to the cover, for example by means of differential thermal expansion, then by placing the cover at the bottom of the opening of the cavity, before allowing the main portion to close again, closing a nesting between a protrusion at the bottom of the cover and a widening at the bottom of the opening. The disadvantages linked to the use of welding, glue or even assembly parts are as such avoided.
Inventors: Guillaume Fribourg, Pierre Delaleau, Florian Tellier
Patent number: 10107129
Abstract: A seal assembly includes a seal arc segment that has first and second seal supports. A carriage has first and second support members. The first support member supports the seal arc segment in a first ramped interface and the second support member supports the seal arc segment in a second ramped interface such that the seal arc segment is circumferentially moveable with respect to the carriage. First and second opposed springs bias the seal arc segment toward a circumferential default position.
Inner diffuser case cone and skirt
Patent number: 10041364
Abstract: An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough. A cone may have a downstream end coupled to the pre-diffuser downstream of, and proximate to, the aperture. A skirt may have a forward end coupled to the pre-diffuser downstream of, and proximate to, the aperture. The forward end of the skirt may be axially aligned with the downstream end of the cone.
Inventors: Jonathan Jeffery Eastwood, Dave J. Hyland, Timothy Dale
Patent number: 10041369
Abstract: This disclosure relates to a gas turbine engine including a blade outer air seal (BOAS) having at least one attachment hook adjacent one of a leading edge and a trailing edge thereof. The BOAS further includes at least one radial standoff axially aligned with the at least one attachment hook.
Inventors: Ken F. Blaney, Brian R. Pelletier, James N. Knapp
Leaf seal reach over spring with retention mechanism
Patent number: 10036269
Abstract: A gas turbine sealing assembly includes a first static gas turbine wall, a second static gas turbine wall, and a leaf seal having a first side and a second side. The first static gas turbine wall contacts the second side at a first position, and the second static gas turbine wall contacts the second side at a second position. A spring exerts force on the first side. The spring includes a first spring wall coupled to the first static gas turbine wall. A second spring wall extends radially outward from the first spring wall. A third spring wall extends axially away from the second spring wall. A fourth spring wall extends radially inward from the third spring wall and includes a radially inner end. The radially inner end of the fourth spring wall contacts the first side of the leaf seal between the first position and the second position.
Inventors: Johnnattan Tennessee Ugarte, Darrell Glenn Senile, Mullahalli Venkataramaniah Srinivas, Jonathon Farmer, Hugh Quill
Compressor assembly having a diffuser ring with tabs
Patent number: 10006341
Abstract: A compressor assembly is disclosed. The compressor assembly may have a compressor housing. The compressor assembly may also have a compressor impeller disposed within the compressor housing. Further, the compressor assembly may have a bearing housing attached to the compressor housing. The compressor assembly may also have a diffuser ring disposed between the compressor housing and the bearing housing. In addition, the compressor assembly may have at least one tab. The tab may extend radially outward from the diffuser ring. The tab may be configured to engage with a recess in the compressor housing. The compressor assembly may also have at least one fastener. The fastener may be configured to attach the diffuser ring and the compressor housing.
Inventors: Richard E. Annati, Robert C. Lancaster, David R. Adair
Fixed vane-type turbocharger
Patent number: 9988939
Abstract: A fixed vane-type turbocharger is provided with a fixed vane in a conduit between a bearing housing and a turbine housing. The fixed vane is configured by a movable member disposed on one of the mutually opposing front faces of the bearing housing and the turbine housing so as to be capable of forward and backward movement, and by vanes which are fixed to the front face of the movable member. A pressing member presses the movable member so that the distal ends of the vanes are brought into pressure contact between the rear face of the movable member and either the bearing housing or the turbine housing with the other opposing front face of these. The pressing member contacts the rear face of the movable member within a range in the radial direction where the vanes are disposed, and presses within this range.
Inventor: Mikito Ishii
System and method for an assembled ring shroud
Patent number: 9970310
Abstract: An assembled ring shroud is provided. The assembled ring shroud may comprise a cover, a first ring layer, a key layer, and a second ring layer. The cover may operatively wrap around, contain, and secure the first ring layer, the key layer, and the second ring layer. The key layer may comprise a key that may act for position and anti-rotation. The key layer may comprise spacers to hold the keys in place. The first ring layer and the second ring layer may be configured to provide further strength and support to the assembled ring shroud.
Inventor: Michael McCaffrey
Heatshield discourager seal for a gas turbine engine
Patent number: 9856746
Abstract: A gas turbine engine includes a service line interface that extends from an outer surface of a bearing support such that a heat shield is spaced from the outer surface. A method of mounting a heat shield to a gas turbine engine includes trapping a heat shield within a gapped overlap spaced from an outer surface of a bearing support.
Inventors: Gary L Grogg, Grace E Szymanski
Consumable assembly mistake proofing tool for a gas turbine engine
Patent number: 9726044
Abstract: A method of assembling a gas turbine engine includes locating a consumable assembly tool clip within the engine.
Inventors: Michael S. Stevens, Timothy M. Davis
Patent number: 9551238
Gas turbine casing load sharing mechanism
Patent number: 9546572
Abstract: A turbine system is provided having a first turbine casing and a second turbine casing, the first and second turbine casings together defining an inner wall. The turbine system further includes a first attachment flange extending from a surface of the first turbine casing within the inner wall and a second attachment flange extending from a surface of the second turbine casing within the inner wall. The first attachment flange defines a first aperture and the second attachment flange defines a second aperture. A pin extends through the first aperture and into the second aperture.
Inventors: Khoa Dang Cao, Kenneth Damon Black
Centerline support bar for steam turbine component
Patent number: 9500130
Abstract: A centerline support bar for steam turbine component assembly, installation, and/or alignment is disclosed. In one embodiment, the support bar includes a body portion configured to be disposed across a centerline of a steam turbine, the body portion configured to transversely connect to a steam turbine component; and a first flange extending from the body portion and configured to contact a steam turbine casing, wherein the steam turbine support bar is configured to non-affixedly join the steam turbine casing to the steam turbine component.
Inventors: Stephen Roger Swan, Matthew Edward Renninger, Kevin John Lewis Roy, Prashant Prabhakar Sankolli
Patent number: 9488063
Stationary blade cascade, assembling method of stationary blade cascade, and steam turbine
Patent number: 9359907
Abstract: A stationary blade cascade 29 of an embodiment includes stationary blade structures 50 and a ring-shaped support structure 40 supporting the stationary blade structures 50. The stationary blade structures 50 each include: a stationary blade part 51 where steam passes; and an outer circumference side constituent part 52 formed on an outer circumference side of the stationary blade part 51 and having a fitting groove 56 which penetrates all along a circumferential direction and which has an opening 55 all along the circumferential direction in a downstream end surface 54 of the outer circumference side constituent part 52. The support structure 40 includes a ring-shaped support part 42 having a fitting portion 41 fitted in the fitting grooves 56 of the outer circumference side constituent parts 52. The plural stationary blade structures 50 are supported along the circumferential direction by the ring-shaped support part 42.
Inventors: Tsuguhisa Tashima, Itaru Murakami, Motoki Yoshikawa
Wear liner spring seal
Patent number: 9353649
Abstract: A wear liner for a stator vane includes a shaped member, comprising a U-shaped portion that receives a foot of a stator vane. A first end of the wear liner is biased into contact with the stator vane. A spring seal extends from the U-shaped portion and into bias contact with an inner surface of the support structure to further prevent leakage between the stator foot and case support structure.
Patent number: 9347456
Assignee: MPC, Inc.
Inventors: William W. Parry, Erik Burachinsky
Patent number: 9303531
Abstract: A quick engine change assembly, comprises a first circular frame member, a plurality of doublet supports spaced about the first circular frame member, the doublet supports being contoured along the axial direction, a flow surface defined between the plurality of doublet supports and, a plurality of cradles, each of the cradles including the doublet supports, the doublet supports from a lower portion of the cradle to the flow surface.
Inventors: William Howard Hasting, Courtney James Tudor
Patent number: 9273563
Abstract: An integrally bladed rotor has an outer rim with a plurality of blades extending radially outwardly of the outer rim. A plurality of channels are formed radially inwardly of the outer rim. A discontinuity formed at a radially outer surface of the outer rim includes a first thin slot at a radially outer face of the outer rim with an enlarged seal holding area. A second thin slot is positioned radially inwardly of the seal holding. The first and second thin slots are thinner circumferentially than the enlarged seal holding area. A seal is inserted into the seal holding area. The seal does not extend into the first and second thin slots, nor into the channels.
Damped assembly
Patent number: 9074478
Abstract: A damped assembly within a gas turbine, comprising a first member and a second member mechanically connected via an intermediate vibration dampener which has at least first and second surfaces for contacting the first and second members respectively, wherein either or both of the first and second surfaces include a plurality of raised portions in direct contact with the respective member and a plurality of recessed portions which contain adhesive for bonding the intermediate vibration dampener to the respective member.
Inventors: Eric P. Ravey, Matthew D. Curren
AIR WITH INTEGRAL SPRING FOR A GAS TURBINE ENGINE EXHAUST DRIVE
Publication number: 20150050127
Abstract: A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface.
Inventors: Christopher J. Peters, Daniel R. Bowers
Publication number: 20150016956
Abstract: One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure.
Inventors: Richard C. Uskert, David J. Thomas, Adam L. Chamberlain
Publication number: 20140314547
Abstract: A first ceramic matrix composite structure having a first flange with a first aperture, and a second structure having a second flange with a second aperture are clamped together by a fastener and spring assembly. The second flange is in contact with the first flange and the apertures of the first and second flanges align with each other. A threaded fastener having a thermal expansion rate that is different than the thermal expansion rate of at least one of the first ceramic matrix composite structure and second structure extends through the aligned apertures. The fastener includes a bolt, a nut, and a spring assembly that maintains a constant clamping pressure irrespective of the thermal expansion differences between the bolt and the first ceramic matrix composite structure and second structure.
Inventors: David J. Sander, Shelton O. Duelm
Patent number: 8657563
Abstract: A sealing assembly is provided for sealing against a component. The sealing assembly comprises a seal carrier and a continuous seal element that is attached to the seal carrier at at least two discrete positions of attachment. The seal element is provided with a sealing surface that is arranged to seal against the component. The seal element is further provided with a thermal expansion slot that is located between the discrete positions of attachment and which extends from a first edge of the seal element over a portion of the width of the seal element. This allows the seal carrier and seal element to thermally expand in the length direction at different rates.
Inventor: Paul R. Hayton
Patent number: 8647048
Abstract: A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections, and a reinforcement member positioned between two of the plurality of corrugate sections.
Inventors: Steven D. Roberts, Richard W. Monahan, David C. Pimenta
Thermal insulation structure for structural member, and scroll structure
Patent number: 8613589
Abstract: To provide a thermal insulation structure for a structural member and a scroll structure which can be easily used even in integrally constructed structural members and which can ensure reliability and thermal insulation properties. Provided are securing portions (52 and 53) extending outward from an outer wall of the structural member; a press plate (55) attached to the securing portions (52 and 53), with a gap between the press plate and the outer wall; and a thermal insulation member (56) disposed between the outer wall and the press plate (55).
EXPANSION JOINT AND STEAM TURBINE SYSTEM INCLUDING THE SAME
Publication number: 20130323027
Abstract: An expansion joint that is provided between a steam turbine outlet and a condenser inlet, including: an upstream baffle tube that has one end secured to an upstream fixing end and the other end as a free end, and forms a steam channel; a downstream baffle tube that has one end secured to a downstream fixed end and the other end as a free end, the free end being relatively movable outside the free end of the upstream baffle tube; and a flexible cylinder that is formed of a non-metal material using a resin sheet, and deformable while airtightly surrounding the baffle tubes.
Inventors: Tsukasa Shimakawa, Jun Nagashima, Yuji Bando, Tomohiro Oshita, Hiromu Nishijima
Turbine ring segment with riffle seal
Patent number: 8585354
Abstract: A blade outer air seal with ring segments forming a mate face gap in which a riffle seal is placed to seal the axial gap. The riffle seal includes a horizontal plate and a vertical plate extending from a bottom surface of the horizontal plate and occupies the axial gap space. The bottom end of the vertical extending plate is angled in a direction of rotation of rotor blades and includes ribs that form open slots in the riffle seal. The ring segments include metering holes that discharge cooling air into the slots to discharge film cooling air onto the hot gas surface of the BOAS and cool the ring segments.
Patent number: 8556578
Abstract: A flexible seal having an X-shaped cross section that forms four contact points on four contact surfaces of two opposed seal slots. The flexible seal is used for a component in which the two seal slots undergo a large deflection such that the opposed slots are not aligned and a rigid seal will not form an adequate seal. The flexible seal can be used in a component of a combustor or a turbine in a gas turbine engine where opposed seal slots undergo the large deflection during operation.
Inventors: Robert L Memmen, John A Fedock, James P Downs
Patent number: 8459936
Abstract: A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections arranged about a centerline, and a connection device secured to the gas turbine engine and to the nozzle structure. The connection device is adjustable to select a length of the flexible annular seal measured along the centerline.
Inventors: Jocelyn Charis Damgaard, Steven D. Roberts, Timothy Dale, Richard W. Monahan, David C. Pimenta