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公开(公告)号：US10689995B2
公开(公告)日：2020-06-23
申请号：US15166805
申请日：2016-05-27
Applicant: General Electric Company
Inventor： Victor John Morgan , Jesse Ellis Barton
Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first portion that is axially offset from the first inner seal and the second inner seal and a second portion abutting the first inner seal and the second inner seal. Also disclosed is an aft frame having a forward face and an aft face. The aft frame includes at least one side seal slot that extends along a side portion. A first portion of the side seal slot is axially offset from the aft face. A second portion of the side seal slot is axially and radially offset from the first portion.
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公开(公告)号：US20180087390A1
公开(公告)日：2018-03-29
申请号：US15275570
申请日：2016-09-26
Applicant: General Electric Company
CPC classification number: F01D9/023 , F02C3/04 , F05D2220/32 , F05D2240/128 , F05D2240/35 , F05D2260/52 , F16J15/0887
Abstract: A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.
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公开(公告)号：US20180058331A1
公开(公告)日：2018-03-01
申请号：US15254037
申请日：2016-09-01
Applicant: General Electric Company
Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. Each of the inner seals includes a wing extending radially inward at an oblique angle. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first wing extending radially outward at an oblique angle and a second wing extending radially outward at an oblique angle, the first wing of the side seal sealingly interfaces with the wing of the first inner seal and the second wing of the side seal sealingly interfaces with the wing of the second inner seal.
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公开(公告)号：US11112037B2
公开(公告)日：2021-09-07
申请号：US15883414
申请日：2018-01-30
Applicant: General Electric Company
Inventor： Luis Armando Sanchez Del Valle , Brian Kenneth Bassett , Robert Scott Phillips , Jesse Ellis Barton , Peter Koppenhoefer , Michael F. Dolan, Jr. , Nathan Lynn Green , Le Yu
Abstract: A hose connection system for connecting a hose to a gas turbine engine. The hose connection system may include a connection fitting and a connection tool. The connection fitting may include a first member to be attached to the gas turbine engine, a mating component to be attached to the hose, and a splined second member to be torqued onto the first member. The connection tool may include a drive wheel with a number of drive wheel splines such that the drive wheel splines torque the splined second member onto the first member.
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公开(公告)号：US10934893B2
公开(公告)日：2021-03-02
申请号：US15779317
申请日：2015-12-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandra Beverly Kolvick , Jeffrey Scott LeBegue , Ansley Michelle Heard , Jesse Ellis Barton , Paul Robert Fernandez , Adrian Adam Klejc
Abstract: A combustor assembly lift system (200) comprises an exterior lift frame (220) comprising a base portion (222) and an arm portion (224), wherein the arm portion extends away from a base portion to form an interior, and, an interior combustor assembly engagement frame (240) at least partially disposed in the interior of the exterior lift frame and configured to temporarily secure to at least a portion of a combustor assembly. The interior combustor assembly engagement frame is connected to the base portion of the exterior lift frame.
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Patent Agency Ranking
公开(公告)号：US20190234541A1
公开(公告)日：2019-08-01
申请号：US15883414
申请日：2018-01-30
Applicant: General Electric Company
Inventor： Luis Armando Sanchez Del Valle , Brian Kenneth Bassett , Robert Scott Phillips , Jesse Ellis Barton , Peter Koppenhoefer , Michael F. Dolan, Jr. , Nathan Lynn Green , Le Yu
CPC classification number: F16L19/02 , F02C7/222 , F05D2230/60 , F05D2240/35 , F23R3/00
Abstract: The present application thus provides a hose connection system for connecting a hose to a gas turbine engine. The hose connection system may include a connection fitting and a connection tool. The connection fitting may include a first member to be attached to the gas turbine engine, a mating component to be attached to the hose, and a splined second member to be torqued onto the first member. The connection tool may include a drive wheel with a number of drive wheel splines such that the drive wheel splines torque the splined second member onto the first member.
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公开(公告)号：US20180023813A1
公开(公告)日：2018-01-25
申请号：US15214751
申请日：2016-07-20
Applicant: General Electric Company
Inventor： Jesse Ellis Barton , Eric Hamann
CPC classification number: F23R3/48 , F02C3/04 , F02C7/26 , F05D2220/32 , F05D2240/35 , F05D2260/30 , F23C6/02 , F23R3/60
Abstract: A crossfire tube assembly is positioned between adjacent combustors, the crossfire tube assembly having a primary body made up of a first telescoping sleeve slidably engaged with a second telescoping sleeve. An interlocking raceway is configured to limit axial travel length of the telescoping sleeves and lock the telescoping sleeves to each other. A bias is positioned between the first telescoping sleeve and the second telescoping sleeve. First and second floating collars are removably disposed to the first and second telescoping sleeves at a first and second floating collar annulus. First and second liner collars are disposed between the first and second floating collars on the first and second combustors. The crossfire tube assembly is adapted to provide fluid communication from the first combustor to the second combustor serving a gas turbine.
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公开(公告)号：US10690059B2
公开(公告)日：2020-06-23
申请号：US15275575
申请日：2016-09-26
Applicant: General Electric Company
Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.
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公开(公告)号：US20180087457A1
公开(公告)日：2018-03-29
申请号：US15275575
申请日：2016-09-26
Applicant: General Electric Company
Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.
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公开(公告)号：US10830069B2
公开(公告)日：2020-11-10
申请号：US15275570
申请日：2016-09-26
Applicant: General Electric Company
Abstract: A sealing arrangement for sealing between a stage-one nozzle and an aft frame includes a seal comprising a flexible sealing element. The flexible sealing element includes an intermediate portion, a first outer portion on one side of the intermediate portion, and a second outer portion on the other side of the intermediate portion. The intermediate portion is mechanically loaded against the first stage nozzle and the aft frame, and the first outer portion and the second outer portion are pressure-loaded against the aft frame and the stage-one nozzle.
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