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公开(公告)号：US09885245B2
公开(公告)日：2018-02-06
申请号：US14283104
申请日：2014-05-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Lorenzo Crosatti , Ardeshir Riahi , Bradley Reed Tucker , Shezan Kanjiyani
CPC classification number: F01D9/02 , F01D9/04 , F01D9/042 , F01D9/065 , F01D25/12 , F01D25/246 , F05D2220/32 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: Turbine nozzles and cooling systems for cooling slip joints therein are provided. The turbine nozzle has an endwall, a vane coupled to the endwall, a slip joint, and a plurality of airfoil quenching holes that cooperate with a plurality of endwall cooling holes. The vane comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall and an end portion. The slip joint is between the end portion and the endwall. The airfoil quenching holes are defined through the pressure sidewall in the end portion. The endwall cooling holes are defined through the endwall along the pressure sidewall and in proximity to the leading edge. The airfoil quenching holes and endwall cooling holes are disposed adjacent the slip joint.
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公开(公告)号：US20160305249A1
公开(公告)日：2016-10-20
申请号：US14687464
申请日：2015-04-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Lorenzo Crosatti , Jason Smoke
CPC classification number: F01D5/087 , F01D5/04 , F01D5/046 , F01D5/048 , F01D5/082 , F01D5/12 , F01D5/34 , F01D25/005 , F01D25/12 , F04D29/28 , F04D29/324 , F04D29/582 , F05D2230/23 , F05D2230/236 , F05D2240/24 , F05D2260/20
Abstract: A rotating machine includes a hub portion, wherein the hub portion comprises a forward face and an aft face. The rotating machine further includes a cooling channel formed on either the forward face or the aft face and configured to direct cooling air to a location on the rotating machine, wherein the cooling channel extends from a radially inner location along said face to a radially outer location along said face, and wherein the cooling channel is configured as a recess formed into an outer surface of said face.
Abstract translation: 旋转机器包括轮毂部分，其中轮毂部分包括前面和后面。 旋转机械还包括形成在前表面或后表面上并构造成将冷却空气引导到旋转机器上的位置的冷却通道，其中冷却通道从沿着所述面的径向内部位置延伸到径向外部位置 沿着所述面，并且其中所述冷却通道被构造成形成在所述面的外表面中的凹部。
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公开(公告)号：US20170254209A1
公开(公告)日：2017-09-07
申请号：US15062952
申请日：2016-03-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , David K. Jan , Amandine Miner , Deanna Pinar Chase , Michael Kahrs , Lorenzo Crosatti
CPC classification number: F01D5/187 , F01D1/08 , F01D5/045 , F01D5/046 , F01D5/3061 , F05D2220/32 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.
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公开(公告)号：US20150275763A1
公开(公告)日：2015-10-01
申请号：US14227924
申请日：2014-03-27
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shezan Kanjiyani , John Gintert , Rajiv Rana , Lorenzo Crosatti , Bradley Reed Tucker , Ed Zurmehly
CPC classification number: F02C7/18 , F01D5/187 , F01D11/08 , F01D25/12 , F01D25/14 , F02C3/10 , F05D2240/81 , F05D2260/201 , F05D2260/205 , Y02T50/673 , Y02T50/676
Abstract: A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.
Abstract translation: 涡轮部分包括具有内径端壁，外径端壁和定子叶片的定子组件; 涡轮转子组件，其包括延伸到主流气流路径中的转子叶片; 壳体，其包括环绕所述转子叶片并且至少部分地限定所述主流热气体流动路径的环形护罩; 第一挡板，布置成限定具有定子组件的外径端壁的第一腔; 第二挡板 以及第三挡板，其布置成限定具有第二挡板的第二空腔和具有护罩的第三空腔。 第一腔体流体地联接到第二腔体，而第二腔室流体耦合到第三空腔，使得冷却空气从第一空腔流到第二空腔，并从第二腔体流到第三空腔。
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5.发明申请公开(公告)号：US20140169957A1
公开(公告)日：2014-06-19
申请号：US13719566
申请日：2012-12-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shezan Kanjiyani , Natalie Wali , Don Mittendorf , Lorenzo Crosatti
CPC classification number: F01D1/04 , B23P11/00 , F01D9/041 , F01D9/042 , F05D2230/60 , F05D2260/941 , Y02T50/671 , Y10T29/49245
Abstract: Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.
Abstract translation: 提供涡轮喷嘴的实施例，如制造涡轮喷嘴的方法的实施例。 在一个实施例中，涡轮喷嘴包括支撑环和滑动接头环，其与支撑环基本上同心并且与其径向间隔开。 滑接环在其中具有多个狭槽。 多个叶片固定地联接到支撑环并且从其径向延伸到多个狭槽中。 在多个叶片和多个槽之间形成多个径向滑动接头。 每个滑动接头围绕多个叶片中的不同的叶片延伸，以允许在涡轮喷嘴的操作期间在多个叶片和滑动接头环之间的相对径向移动。
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Patent Agency Ranking
公开(公告)号：US10260355B2
公开(公告)日：2019-04-16
申请号：US15062952
申请日：2016-03-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , David K Jan , Amandine Miner , Deanna Pinar Chase , Michael Kahrs , Lorenzo Crosatti
Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.
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公开(公告)号：US09896943B2
公开(公告)日：2018-02-20
申请号：US14275012
申请日：2014-05-12
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Lorenzo Crosatti , Shezan Kanjiyani , Don Mittendorf
CPC classification number: F01D5/189 , B22F3/1055 , B22F5/009 , B22F5/04 , B22F7/004 , F01D5/147 , F01D5/183 , F01D5/186 , F01D5/188 , F05D2260/202 , F05D2260/203 , Y02P10/295 , Y02T50/676 , Y10T29/49321
Abstract: Gas path components of gas turbine engines and methods for cooling the same using porous medium cooling systems are provided. The gas path component comprises a wall at least partially defining a cooling plenum and a porous medium cooling system. The wall includes a wall surface comprising a gas path surface and an opposing wall surface proximate the cooling plenum. The porous medium cooling system is disposed between the cooling plenum and the opposing wall surface. The porous medium cooling system comprises a perforated baffle and a porous material layer disposed between and adjacent the perforated baffle and the opposing wall surface. The wall includes a plurality of openings in fluid communication with the cooling plenum via the porous medium cooling system.
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公开(公告)号：US09702252B2
公开(公告)日：2017-07-11
申请号：US13719566
申请日：2012-12-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shezan Kanjiyani , Natalie Wali , Don Mittendorf , Lorenzo Crosatti
CPC classification number: F01D1/04 , B23P11/00 , F01D9/041 , F01D9/042 , F05D2230/60 , F05D2260/941 , Y02T50/671 , Y10T29/49245
Abstract: Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.
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公开(公告)号：US09850760B2
公开(公告)日：2017-12-26
申请号：US14687464
申请日：2015-04-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Lorenzo Crosatti , Jason Smoke
IPC: F01D5/08 , F04D29/32 , F01D5/04 , F01D5/12 , F04D29/28 , F04D29/58 , F01D25/12 , F01D25/00 , F01D5/34
CPC classification number: F01D5/087 , F01D5/04 , F01D5/046 , F01D5/048 , F01D5/082 , F01D5/12 , F01D5/34 , F01D25/005 , F01D25/12 , F04D29/28 , F04D29/324 , F04D29/582 , F05D2230/23 , F05D2230/236 , F05D2240/24 , F05D2260/20
Abstract: A rotating machine includes a hub portion, wherein the hub portion comprises a forward face and an aft face. The rotating machine further includes a cooling channel formed on either the forward face or the aft face and configured to direct cooling air to a location on the rotating machine, wherein the cooling channel extends from a radially inner location along the face to a radially outer location along the face, and wherein the cooling channel is configured as a recess formed into an outer surface of the face.
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公开(公告)号：US20150082808A1
公开(公告)日：2015-03-26
申请号：US13855417
申请日：2013-04-02
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Daniel Cregg Crites , Mark C. Morris , Lorenzo Crosatti , Ardeshir Riahi
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
Abstract: An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
Abstract translation: 提供了一种用于燃气涡轮发动机的翼型件。 翼型件包括具有前缘的主体，后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。 身体定义一个内腔。 所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸的内壁，以限定供应室和前缘室。 内壁限定具有基部和局部延伸部分的冷却孔，以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。
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