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No. Publication Number Title Publication/Patent Number Publication/Patent Number Publication Date Publication Date
Application Number Application Number Filing Date Filing Date
Inventor Inventor Assignee Assignee IPC IPC
1 US10526899B2
Turbine blade having a tip shroud
Publication/Patent Number: US10526899B2 Publication Date: 2020-01-07 Application Number: 15/431,981 Filing Date: 2017-02-14 Inventor: Zemitis, William Scott   Pasupuleti, Mahesh   Lewis, Bryan David   Myers, Melbourne James   Assignee: General Electric Company   IPC: F01D5/22 Abstract: A turbine blade includes an airfoil that extends from a root end to a tip end. A tip shroud extends from the tip end. The turbine blade further includes a pressure side fillet. The pressure side fillet couples the tip end to the tip shroud. The pressure side fillet includes a first protrusion located adjacent to the tip end and a second protrusion located radially inward from the first protrusion. A turbine blade includes an airfoil that extends from a root end to a tip end. A tip shroud extends from the tip end. The turbine blade further includes a pressure side fillet. The pressure side fillet couples the tip end to the tip shroud. The pressure side fillet includes a ...More ...Less
2 US10544687B2
Shrouded blade of a gas turbine engine
Publication/Patent Number: US10544687B2 Publication Date: 2020-01-28 Application Number: 15/645,021 Filing Date: 2017-07-10 Inventor: Skura, Krzysztof   Lebiedowicz, Piotr   Szponar, Marek   Assignee: MTU Aero Engines AG   IPC: F01D5/22 Abstract: The present invention relates to an improved cast-to-size gas turbine blade comprising a blade tip shroud with a stiffening rib extending outwardly from the section of the outer side of the shroud platform located between the upstream sealing fin and the upstream edge. The stiffening rib having substantially planar top surface in form of a trapezium, and two sloping sidewalls extending between the upstream sealing fin and the upstream edge on each side of the top surface and connecting said top surface with adjacent surface of the outer side of the shroud platform. The form of the stiffening rib allows to obtain an improved shroud configuration of reduced overall blade mass, capable of providing sufficient stiffening of the shroud, reducing vibrations of the shroud platform, creep curling of the shroud edges and bending stress at the intersection of the airfoil and of the shroud. The present invention relates to an improved cast-to-size gas turbine blade comprising a blade tip shroud with a stiffening rib extending outwardly from the section of the outer side of the shroud platform located between the upstream sealing fin and the upstream edge. The ...More ...Less
3 US10648353B2
Low loss airfoil platform rim seal assembly
Publication/Patent Number: US10648353B2 Publication Date: 2020-05-12 Application Number: 14/942,484 Filing Date: 2015-11-16 Inventor: Aggarwala, Andrew S.   Bergman, Russell J.   Boeke, Mark A.   Lana, Kyle C.   Snyder, Daniel A.   Assignee: United Technologies Corporation   IPC: F01D11/02 Abstract: An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity. An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of ...More ...Less
4 US10655478B2
Turbine blade and gas turbine
Publication/Patent Number: US10655478B2 Publication Date: 2020-05-19 Application Number: 15/569,247 Filing Date: 2016-08-08 Inventor: Takamura, Keita   Hada, Satoshi   Atsumi, Hidekatsu   Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.   IPC: F01D5/18 Abstract: A blade main body (51) of a gas turbine is provided with a first cooling passage part (58), a second cooling passage part (59), a column part (60), and a plurality of protrusions. The first cooling passage part (58) is provided at the side near to a leading edge (55). The second cooling passage part (59) is provided at the side near to a trailing edge (56). The column part (60) is provided between the first cooling passage part (58) and the second cooling passage part (59), and is continuously formed between a base part and an end part of the blade main body (51). The protrusions protrude from the inner wall surfaces of the first cooling passage part (58) and the second cooling passage part (59). A blade main body (51) of a gas turbine is provided with a first cooling passage part (58), a second cooling passage part (59), a column part (60), and a plurality of protrusions. The first cooling passage part (58) is provided at the side near to a leading edge (55). The second ...More ...Less
5 US10605099B2
Cooling arrangements in turbine blades
Publication/Patent Number: US10605099B2 Publication Date: 2020-03-31 Application Number: 15/745,165 Filing Date: 2015-07-31 Inventor: Taylor, Zachary James   Wedmore, Lucas Seth   Mistry, Hiteshkumar Rameshchandra   Assignee: General Electric Company   IPC: F01D5/18 Abstract: A rotor blade (16) for a turbine of a gas turbine that includes an airfoil (25). The airfoil may have a leading edge, a trailing edge, an outboard tip, and an inboard end where the airfoil attaches to a root configured to couple the turbine blade to a rotor disc. The airfoil (25) may include a tip shroud (55) at an outboard tip. The rotor blade may have a cooling configuration that includes: elongated cooling channels (33) for receiving and directing a coolant through the airfoil (25); and branching passages (75) formed through the tip shroud (55), each of which elongates between a connection with one of the cooling channels (33) and an outlet port (37) formed on a surface of the tip shroud (55). The branching passages (75) may have a canted orientation relative the outboard surface of the tip shroud (55). A rotor blade (16) for a turbine of a gas turbine that includes an airfoil (25). The airfoil may have a leading edge, a trailing edge, an outboard tip, and an inboard end where the airfoil attaches to a root configured to couple the turbine blade to a rotor disc. The airfoil ...More ...Less
6 EP2985419B1
TURBOMACHINE BLADE ASSEMBLY WITH BLADE ROOT SEALS
Publication/Patent Number: EP2985419B1 Publication Date: 2020-01-08 Application Number: 15175919.8 Filing Date: 2015-07-08 Inventor: Mccaffrey, Michael G.   Assignee: United Technologies Corporation   IPC: F01D5/22
7 EP3597862A1
FAN PLATFORM WEDGE SEAL
Publication/Patent Number: EP3597862A1 Publication Date: 2020-01-22 Application Number: 19186635.9 Filing Date: 2019-07-16 Inventor: Kling, Colin J.   Assignee: United Technologies Corporation   IPC: F01D5/22 Abstract: A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms (106) are positioned intermediate blade sides (122) of adjacent ones of the fan blades (102). Seals (124) are positioned between the blade sides (122) and platform sides (120) of the platforms (106). The seals (124) have an elongated attachment portion (126) bonded to one of the platform sides (120) and the blade sides (122). The seal (124) extends radially outwardly from the elongated attachment portion (126) to a wedge portion (134). A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms (106) are positioned intermediate blade sides (122) of adjacent ones of the fan blades (102). Seals (124) are positioned between the blade sides (122) and ...More ...Less
8 EP2161409B1
Steam turbine rotating blade for a low pressure section of a steam turbine engine
Publication/Patent Number: EP2161409B1 Publication Date: 2020-03-18 Application Number: 09168948.9 Filing Date: 2009-08-28 Inventor: Demania, Alan Richard   Riaz, Muhammad Saqib   Assignee: General Electric Company   IPC: F01D5/14
9 EP2519721B1
DAMPER SEAL
Publication/Patent Number: EP2519721B1 Publication Date: 2020-03-11 Application Number: 10846805.9 Filing Date: 2010-12-29 Inventor: Gilman, Justin   Assignee: Rolls-Royce Corporation   IPC: F02C3/02
10 US2020166143A1
ASPIRATING FACE SEAL ASSEMBLY FOR A ROTARY MACHINE
Publication/Patent Number: US2020166143A1 Publication Date: 2020-05-28 Application Number: 16/201,669 Filing Date: 2018-11-27 Inventor: Tran, Quang Tue Nguyen   Gibson, Nathan Evan Mccurdy   Erdmenger, Rodrigo Rodriguez   Wolfe, Christopher Edward   Johnson, Steven Douglas   Valencia, Antonio Guijarro   Assignee: General Electric Company   IPC: F16J15/44 Abstract: A seal assembly for a rotary machine includes a seal bearing face that opposes a rotating component of the machine and a slide device coupled with the seal bearing face. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing includes feed ports. The feed ports extend through the seal bearing face to form aerostatic portions of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component has a non-planar surface that, during rotating motion of the rotating component relative to the face of the seal bearing face, forms aerodynamic portions of the film bearing. A seal assembly for a rotary machine includes a seal bearing face that opposes a rotating component of the machine and a slide device coupled with the seal bearing face. The slide device axially moves toward the rotating component responsive to pressurization of the rotary ...More ...Less
11 EP2414640B1
BLADE FOR A GAS TURBINE
Publication/Patent Number: EP2414640B1 Publication Date: 2020-05-27 Application Number: 10706671.4 Filing Date: 2010-03-05 Inventor: Zambetti, Chiara   Riazantsev, Sergei   Saxer-felici, Héléne   Assignee: Ansaldo Energia IP UK Limited   IPC: F01D5/22
12 EP3653844A1
STRIP SEAL, ANNULAR SEGMENT AND METHOD FOR A GAS TURBINE
Publication/Patent Number: EP3653844A1 Publication Date: 2020-05-20 Application Number: 18206450.1 Filing Date: 2018-11-15 Inventor: Overton, David   Welburn, Peter   Assignee: Siemens Aktiengesellschaft   IPC: F01D11/00 Abstract: The present invention relates to a strip seal (200) for use in a gas turbine, in particular for sealing the gap between adjacent turbine vane platforms (320), comprising an elongated main body (220) defining a longitudinal direction, the main body (220) comprising first and second ends (221, 222) delimiting the main body (220) along the longitudinal direction, and a cavity (240) defined by the main body (220). The strip seal (200) further comprises a locking member (260) projecting away from the main body (220) and may be resiliently deformed to be contained in said cavity (240). The strip seal (200) may be maintained in a linear track (362) being formed in a turbine vane platform (320) having a recess (366) for receiving said locking member (260). Thereby, assembly of the vane ring may be faster and more convenient and the strip seal (200) may be recovered in substantially undamaged condition. The present invention relates to a strip seal (200) for use in a gas turbine, in particular for sealing the gap between adjacent turbine vane platforms (320), comprising an elongated main body (220) defining a longitudinal direction, the main body (220) comprising first and ...More ...Less
13 US10590777B2
Turbomachine rotor blade
Publication/Patent Number: US10590777B2 Publication Date: 2020-03-17 Application Number: 15/638,571 Filing Date: 2017-06-30 Inventor: Brittingham, Robert Alan   Assignee: General Electric Company   IPC: F01D5/22 Abstract: The present disclosure is directed to a rotor blade that includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a cooling core in fluid communication with the cooling passage. The cooling core includes a first cooling channel and a second cooling channel. The first cooling channel is radially spaced apart from the second cooling channel. Coolant flows in a first direction through the first cooling channel and in a second direction through the second cooling channel. The first direction is different than the second direction. The present disclosure is directed to a rotor blade that includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a cooling core in fluid communication with the cooling passage. The cooling core includes a ...More ...Less
14 EP2378068B1
DAMPING SYSTEM FOR DAMPING VIBRATIONS OF A ROTOR BLADE, CORRESPONDING ROTOR BLADE AND ROTOR
Publication/Patent Number: EP2378068B1 Publication Date: 2020-04-29 Application Number: 11161054.9 Filing Date: 2011-04-04 Inventor: Borufka, Hans Peter   Hartung, Andreas   Prokopczuk, Patrick   Stiehler, Frank   Assignee: MTU Aero Engines AG   IPC: F01D5/02
15 EP3643879A2
ROTOR ASSEMBLY WITH STRUCTURAL PLATFORMS FOR GAS TURBINE ENGINES
Publication/Patent Number: EP3643879A2 Publication Date: 2020-04-29 Application Number: 19203663.0 Filing Date: 2019-10-16 Inventor: Husband, Jason   Glaspey, James   Assignee: United Technologies Corporation   IPC: F01D5/14 Abstract: A platform (370, 470) for a gas turbine engine includes a platform body (388, 488) that extends in a circumferential direction between first and second sidewalls (390, 490) to define a gas path surface (391), and opposed rows of flexible retention tabs that extend from the platform body (388, 488) and are dimensioned to wedge the platform (370, 470) between adjacent airfoils (66, 166, 266, 366). A platform (370, 470) for a gas turbine engine includes a platform body (388, 488) that extends in a circumferential direction between first and second sidewalls (390, 490) to define a gas path surface (391), and opposed rows of flexible retention tabs that extend from the ...More ...Less
16 EP3392464B1
SEALING RING MEMBER FOR A TURBINE COMPRISING AN ANGLED CAVITY MADE OF AN ABRADABLE MATERIAL
Publication/Patent Number: EP3392464B1 Publication Date: 2020-03-25 Application Number: 18167088.6 Filing Date: 2018-04-12 Inventor: Telman, Cyrille   Lambert, Olivier Arnaud Fabien   Ricou, Laurent Pierre Joseph   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F01D11/12
17 EP3187688B1
ROTOR BLADE FOR A GAS TURBINE AND CORRESPONDING GAS TURBINE
Publication/Patent Number: EP3187688B1 Publication Date: 2020-03-18 Application Number: 16203546.3 Filing Date: 2016-12-12 Inventor: Mcdufford, Michael David   Assignee: General Electric Company   IPC: F01D5/22
18 EP3615774A1
DEVICE FOR SEALING BETWEEN A ROTOR AND A STATOR OF A TURBINE ENGINE
Publication/Patent Number: EP3615774A1 Publication Date: 2020-03-04 Application Number: 18725281.2 Filing Date: 2018-04-24 Inventor: Jouy, Baptiste Marie Aubin Pierre   Sicard, Josselin Luc Florent   Verdiere, Mathieu Charles Jean   Villard, Loïc Fabien François   Assignee: Safran Aircraft Engines   IPC: F01D11/08