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公开(公告)号：WO2014193509A8
公开(公告)日：2015-10-15
申请号：PCT/US2014021975
申请日：2014-03-07
Applicant: GEN ELECTRIC
Inventor： ALBERS JOSEPH C , SHELTON MONTY LEE , PROCTOR ROBERT , RUSSO RICHARD JR
CPC classification number: F01D11/122 , F01D11/005 , F01D11/127 , F01D25/246 , F02C7/28 , F05D2220/32 , F05D2240/11 , F05D2240/57 , Y02T50/671
Abstract: A turbine shroud assembly comprises a honeycomb rub strip, a metallic backsheet disposed along an upper edge of said honeycomb seal structure, a shroud frame having a first rail and a second rail disposed at lateral edges of said metallic backsheet, a first support and a second support connected to the first rail and the second rail, a spline extending axially in the first rail and the second rail along laterally outer surfaces of the first rail and the second rail and, a spline seal having a first edge and a second opposite edge, the first edge disposed in each of the spline grooves and the second opposite edge being capable of positioning in an adjacent shroud assembly.
Abstract translation: 涡轮机罩组件包括蜂窝状擦拭条，沿着所述蜂窝状密封结构的上边缘设置的金属底片，具有设置在所述金属底片的侧边缘处的第一轨道和第二轨道的护罩框架，第一支撑件和第二支撑件 连接到第一轨道和第二轨道的支撑件，沿第一轨道和第二轨道的横向外表面在第一轨道和第二轨道中轴向延伸的花键，以及具有第一边缘和第二相对边缘的花键密封件， 设置在每个花键槽中的第一边缘和第二相对边缘能够定位在相邻的护罩组件中。
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公开(公告)号：WO2014193509A3
公开(公告)日：2015-01-22
申请号：PCT/US2014021975
申请日：2014-03-07
Applicant: GEN ELECTRIC
Inventor： ALBERS JOSEPH C , SHELTON MONTY LEE , PROCTOR ROBERT , RUSSO RICHARD
CPC classification number: F01D11/122 , F01D11/005 , F01D11/127 , F01D25/246 , F02C7/28 , F05D2220/32 , F05D2240/11 , F05D2240/57 , Y02T50/671
Abstract: A turbine shroud assembly comprises a honeycomb rub strip, a metallic backsheet disposed along an upper edge of said honeycomb seal structure, a shroud frame having a first rail and a second rail disposed at lateral edges of said metallic backsheet, a first support and a second support connected to the first rail and the second rail, a spline extending axially in the first rail and the second rail along laterally outer surfaces of the first rail and the second rail and, a spline seal having a first edge and a second opposite edge, the first edge disposed in each of the spline grooves and the second opposite edge being capable of positioning in an adjacent shroud assembly.
Abstract translation: 涡轮护罩组件包括蜂窝摩擦条，沿所述蜂窝密封结构的上边缘设置的金属底片，具有第一轨道和设置在所述金属底片的侧边缘处的第二轨道的护罩框架，第一支撑件和第二支撑件 支撑件，所述支撑件连接到所述第一导轨和所述第二导轨;花键，所述花键在所述第一导轨和所述第二导轨中沿所述第一导轨和所述第二导轨的横向外表面轴向延伸;以及花键密封件，其具有第一边缘和第二相对边缘， 第一边缘设置在每个花键凹槽中，并且第二相对边缘能够定位在相邻的护罩组件中。
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公开(公告)号：JP2002004805A
公开(公告)日：2002-01-09
申请号：JP2001107880
申请日：2001-04-06
Applicant: GEN ELECTRIC
Inventor： GONYOU CRAIG ALAN , DOUGHTY ROGER LEE , SHELTON MONTY LEE
Abstract: PROBLEM TO BE SOLVED: To provide a gas turbine engine cooling constitution part for cooling an end rail. SOLUTION: The turbine cooling constitution part divided into segments, such as a shroud segment for the high-pressure and low-pressure turbine section of a gas turbine, is served to apply preferential cooling on the side rail or the panel of the turbine constitution part, by applying impingement cooling on a side panel below a damping seal by air in the position of a recess formed in the bottom wall surface of a lower damping seal, through the combination of cooling air fed in an intermediate pressure cavity between the damping seal and a main seal. The side panel of the turbine constitution part has a lower damping seal slot provided with an upper main seal slot, a bottom wall having a plurality of lands and recesses, changing places with each other along the direction of its length, and a plurality of air cooling passages, each having an outlet which opens in a lower slot and at a position above the land.
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公开(公告)号：JP2002054459A
公开(公告)日：2002-02-20
申请号：JP2001140808
申请日：2001-05-11
Applicant: GEN ELECTRIC
Inventor： WALLACE THOMAS TRACY , GLYNN CHRISTOPHER CHARLES , SHELTON MONTY LEE , CLEMENTS JEFFREY DONALD , LENAHAN DEAN T , KALB BARRY JOHN
Abstract: PROBLEM TO BE SOLVED: To provide a method and device for directing air flow to a compressor bore. SOLUTION: A gas turbine rotor assembly contains a plurality of aerodynamic devices to direct a flow of air to the inside in a radial direction. The gas turbine engine rotor assembly contains a rotor shaft having a plurality of openings. An aerodynamic device contains a pair of blade segments and a pair of side walls. An outside surface having a contour shape contains an opening and the aerodynamic device can be installed in a manner to make contact with the inside surface of the rotor shaft and a flange ring demarcates a pocket. The aerodynamic device is fitted in the inside of the pocket with the openings adjusted to concentricity.
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公开(公告)号：JP2002349287A
公开(公告)日：2002-12-04
申请号：JP2002077552
申请日：2002-03-20
Applicant: GEN ELECTRIC
Inventor： GLYNN CHRISTOPHER CHARLES , WALLACE THOMAS TRACY , DICKMAN RONALD ARTHUR , SHELTON MONTY LEE
Abstract: PROBLEM TO BE SOLVED: To provide a turbine cooling circuit 32 including a passage sleeve 34 having the rear end 36 adjacent to a rim 30a of a turbine disc 30. SOLUTION: Seal rotors 38 and 42 are separately arranged from the rear end, and are adjacent to a row of an inlet hole 40. An inducer 46 has an outlet 50 arranged on the radial directional outside of a sleeve inlet hole. Seal stators 52 and 54 surround the seal rotors, and form a rotary seal arranged on the radial directional inside of an inducer outlet.
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Patent Agency Ranking
公开(公告)号：JPH1172006A
公开(公告)日：1999-03-16
申请号：JP16968498
申请日：1998-06-17
Applicant: GEN ELECTRIC
Inventor： SAVAGE JOSEPH WALTER , HALILA ELY ESKENAZI , ORLANDO ROBERT JOSEPH , BOEHM JR VALENTINE ROBERT , MARTUS JAMES ARTHUS , WALLACE THOMAS TRACY , SHELTON MONTY LEE
Abstract: PROBLEM TO BE SOLVED: To provide a variable area turbine nozzle which can selectively vary an area of a neck portion. SOLUTION: A turbine nozzle has a plurality of nozzle segments 14 adjacently arranged in a circumferential direction. The nozzle segments are first blade segments 22 arranged between spaced outer and inner bands 16 and 18 and second blade segments 24 arranged adjacently to the first blade segments 22 to compose a plurality of corresponding blades with them. Throat portions 26 of a minimum flow area are formed among the plural blades for passing combustion gas on the second blade segment. A turning means 28 is arranged for turning the second blade segment and varying an area of the neck portion.
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公开(公告)号：JP2002235503A
公开(公告)日：2002-08-23
申请号：JP2002001867
申请日：2002-01-09
Applicant: GEN ELECTRIC
Inventor： LEE CHING-PANG , PRAKASH CHANDER , SHELTON MONTY LEE , STARKWEATHER JOHN HOWARD , SINGH HARDEV , RINCK GERARD ANTHONY
Abstract: PROBLEM TO BE SOLVED: To provide a rotor blade 40 for a gas turbine engine 10 including a tip region 60 for promoting decrease in yield temperature of the rotor blade. SOLUTION: The tip region includes a first tip wall 62 and a second tip wall 64 extending radially and outwardly from a tip blade 54 of a profile part 42. The tip wall extends from the proximity of the leading edge 48 of the profile part, and is connected through the trailing edge 50 of the profile part. A notch 80 is formed between first and second tip walls at the leading edge of the profile part. At least a part of the second tip wall is dented to form a tip shelf part 90.
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公开(公告)号：JP2001227302A
公开(公告)日：2001-08-24
申请号：JP2000381168
申请日：2000-12-15
Applicant: GEN ELECTRIC
Inventor： DARKINS TOBY GEORGE JR , SHELTON MONTY LEE , DOUGHTY ROGER LEE , NOE MARK EUGENE
IPC: F01D9/02 , C04B35/565 , F01D5/18 , F01D5/28
Abstract: PROBLEM TO BE SOLVED: To provide an improved turbine vane type part and a nozzle stationary blade conforming to stress and temperature conditions under a high temperature and a high pressure circumstances and imparting strength and cooling characteristic enough to use a ceramic material low in thermal gradient capacity. SOLUTION: The hollow turbine vane type part 12 of a gas turbine engine includes an external wall 40 to surround a hollow inner part 22, the external wall extends outward in the radial direction from a base part 46 of the vane type part to a head end 48, it has a front edge and a rear edge separated from each other in the chord direction and pressure side and suction side parts 52, 54 extending in the chord direction between the front edge and a rear edge block 50 and separated from each other in the cross direction, and the rear edge block ends at the rear edge. A plural number of rear edge cooling air ducts 60 pass through the rear edge block backward in the chord direction from the hollow inner part 22, and a plural number of rear edge film cooling holes 62 pass through the rear edge block from the ducts 60. The ducts favourably have their centers in the neighborhood of a neutral axis 64 of bending in the chord direction and the vane cross direction of the rear edge block. The ducts are tapered from the hollow inner part backward, and their width gradually decreases by having roughly constant height in the vane cross direction.
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公开(公告)号：CA2891616A1
公开(公告)日：2014-05-30
申请号：CA2891616
申请日：2013-10-15
Applicant: GEN ELECTRIC
Inventor： ALBERS JOSEPH CHARLES , PROCTOR ROBERT , SHELTON MONTY LEE , RUSSO RICHARD JR
Abstract: A turbine shroud apparatus for a gas turbine engine having a centerline axis includes: a shroud segment having: an arcuate body extending axially between forward and aft ends and laterally between opposed end faces, wherein each of the end faces includes seal slots formed therein; and an arcuate stationary seal member mounted to the body; a turbine vane disposed axially aft of the shroud segment; and a casing surrounding the shroud segment and the turbine vane; wherein the turbine vane is mounted to the case so as to bear against the stationary seal member, compressing it and forcing the shroud segment radially outward against the casing.
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公开(公告)号：ES2288499T3
公开(公告)日：2008-01-16
申请号：ES01304245
申请日：2001-05-11
Applicant: GEN ELECTRIC
Inventor： WALLACE THOMAS TRACY , SHELTON MONTY LEE , LENAHAN DEAN THOMAS , GLYNN CHRISTOPHER CHARLES , CLEMENTS JEFFREY DONALD , KALB BARRY JOHN
Abstract: Un conjunto (42) de rotor para un motor (10) de turbina de gas, comprendiendo dicho conjunto de rotor un árbol (44) de rotor que comprende una superficie (50) interior y una superficie (48) exterior; comprendiendo además el árbol de rotor una pluralidad de primeras aberturas (52) que se extienden entre la superficie (50) interior y la superficie (48) exterior; y, una pluralidad de dispositivos (66) aerodinámicos que se extienden de manera circunferencial dentro de dicho árbol de rotor y configurados para redirigir flujo (70) de aire a través de dicho árbol (44) de rotor, caracterizado porque cada uno de dichos dispositivos aerodinámicos comprende una segunda abertura (74) que se extiende a través de los mismos alineada de manera circunferencial con dicha primera abertura y que puede moverse de manera radial dentro del árbol (44) de rotor durante la rotación de dicho árbol de rotor.
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