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公开(公告)号：US20170356304A1
公开(公告)日：2017-12-14
申请号：US15181070
申请日：2016-06-13
发明人： Richard Schmidt
CPC分类号： F01D25/10 , F01D25/04 , F01D25/20 , F02C7/06 , F02C7/224 , F05D2220/32 , F05D2260/20 , F05D2260/98 , H05B6/06 , H05B6/108 , Y02T50/675
摘要： A fluid viscosity system for use in a gas turbine engine includes an induction assembly coupled to a fluid line within the gas turbine engine. The induction assembly includes an electromagnet. The induction assembly further includes an electronic oscillator electronically coupled to the electromagnet. The electronic oscillator is configured to generate an alternating current (AC) that is transmitted to the electromagnet at a predetermined frequency and magnitude such that a viscosity of a fluid channeled through the fluid line is reduced at least partially due to induction heating.
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公开(公告)号：US20170334010A1
公开(公告)日：2017-11-23
申请号：US15656063
申请日：2017-07-21
IPC分类号： B23K9/04 , F23R3/00 , B23K9/173 , F02C7/22 , F01D5/22 , B23P15/04 , F01D5/28 , B23K9/32 , F01D5/12 , B23P15/02 , F01D5/18 , B23K103/18 , B23K101/00 , F01D5/00
CPC分类号： B23K9/044 , B23K9/048 , B23K9/173 , B23K9/32 , B23K2101/001 , B23K2103/26 , B23P15/02 , B23P15/04 , B23P2700/06 , F01D5/005 , F01D5/12 , F01D5/186 , F01D5/225 , F01D5/286 , F02C7/22 , F05D2230/12 , F05D2230/80 , F05D2260/20 , F23R3/002 , Y10T428/13 , Y10T428/24273
摘要： A method for modifying an aperture in a component, a system for modifying flow through a component, and a turbine component are disclosed. The method includes providing a substrate having at least one aperture having an electrically-conductive surface, providing a deposition device including an ESD torch, the ESD torch including an aperture penetrating electrode including a conductive material, inserting the aperture penetrating electrode at least partially into the aperture, and generating an arc between the aperture penetrating electrode and the electrically-conductive surface to deposit electrode material within the aperture. The system includes the ESD torch removably supported in an electrode holder. The turbine component includes at least one aperture having an electrospark deposited material along an electrically-conductive surface, the electrospark deposited material providing modified fluid flow through the turbine component.
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公开(公告)号：US09810151B2
公开(公告)日：2017-11-07
申请号：US14512070
申请日：2014-10-10
申请人： Joseph D Brostmeyer
发明人： Joseph D Brostmeyer
CPC分类号： F02C7/18 , F01D5/082 , F05D2220/3215 , F05D2260/20
摘要： A turbine of a gas turbine engine with a rotor and a stator forming a rim cavity, where the rotor includes a turbine rotor blade with a cooling air channel opening into the rim cavity, and a centrifugal impeller rotatably connected to the rotor in which the centrifugal impeller discharges pressurized cooling air into the rim cavity to improve the rim cavity seal and to supply pressurized cooling air to the rotor blade cooling air channel.
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公开(公告)号：US09810087B2
公开(公告)日：2017-11-07
申请号：US14748876
申请日：2015-06-24
CPC分类号： F01D11/006 , F01D5/081 , F01D5/22 , F01D5/3015 , F01D11/008 , F02C7/18 , F05D2220/32 , F05D2240/24 , F05D2240/55 , F05D2250/72 , F05D2260/20 , F16J15/02 , Y02T50/676
摘要： A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a second condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.
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公开(公告)号：US09803502B2
公开(公告)日：2017-10-31
申请号：US14617506
申请日：2015-02-09
发明人： Anthony P. Cherolis , Jeffrey J. Lienau , Robert Newman , John H. Mosley , Joshua Daniel Winn , Paul K. Sanchez
CPC分类号： F01D25/14 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/24 , F02C7/12 , F05D2220/32 , F05D2220/3213 , F05D2260/20 , F05D2260/31 , Y02T50/676
摘要： A mid-turbine frame assembly includes an inner frame case which includes a first plurality of holes and a second plurality of holes. A plurality of tie rods is circumferentially spaced around the inner frame case and includes an inlet passage that is aligned with the first plurality of holes. A plurality of hollow airfoils is aligned with the second plurality of holes.
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公开(公告)号：US09803486B2
公开(公告)日：2017-10-31
申请号：US14144939
申请日：2013-12-31
CPC分类号： F01D9/02 , C04B37/005 , C04B2237/083 , C04B2237/365 , C04B2237/38 , C04B2237/61 , C04B2237/76 , C04B2237/84 , F01D5/189 , F01D5/284 , F01D5/288 , F01D9/041 , F01D9/044 , F05D2260/20 , F05D2300/211 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.
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公开(公告)号：US20170306844A1
公开(公告)日：2017-10-26
申请号：US15492376
申请日：2017-04-20
CPC分类号： F02C3/34 , F01K7/16 , F01K25/103 , F02C1/04 , F02C3/30 , F02C7/10 , F05D2240/35 , F05D2260/20 , F05D2260/61
摘要： The present disclosure relates to systems and methods wherein a dilute hydrocarbon stream can be oxidized to impart added energy to a power production system. The oxidation can be carried out without substantial combustion of the hydrocarbons. In this manner, dilute hydrocarbon streams that would otherwise be required to undergo costly separation processes can be efficiently utilized for improving the power production system and method. Such systems and methods particularly can utilize dilute hydrocarbon stream including a significant amount of carbon dioxide, such as may be produced in hydrocarbon recovery process, such as enhanced oil recovery or conventional hydrocarbon recovery processes.
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公开(公告)号：US20170298762A1
公开(公告)日：2017-10-19
申请号：US14615509
申请日：2015-02-06
CPC分类号： F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.
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公开(公告)号：US09771814B2
公开(公告)日：2017-09-26
申请号：US14641470
申请日：2015-03-09
发明人： Brandon W. Spangler , Ky H. Vu , Jeffrey J. DeGray , Ryan Alan Waite , Gina Cavallo , Thomas P. Dziuba
CPC分类号： F01D9/041 , F01D5/02 , F01D5/186 , F01D5/189 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2230/21 , F05D2230/642 , F05D2240/126 , F05D2240/80 , F05D2260/20 , F05D2260/30 , Y02T50/676
摘要： A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.
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公开(公告)号：US20170260864A1
公开(公告)日：2017-09-14
申请号：US15069738
申请日：2016-03-14
发明人： Jeffrey Leon , Daniel C. Nadeau , Jeffrey R. Levine , Eleanor D. Kaufman , Richard N. Allen , Evan P. Molony , Gregory Anselmi
CPC分类号： F01D5/187 , B22C9/10 , F02C7/18 , F05D2220/32 , F05D2260/20 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.
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