公开(公告)号：US20160146024A1

公开(公告)日：2016-05-26

申请号：US14551293

申请日：2014-11-24

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Mark C. Morris ,  Daira Legzdina ,  Don Mittendorf ,  Milton Ortiz ,  Ardeshir Riahi ,  Michael Vinup

IPC: F01D5/30 ,  F01D5/28 ,  B23K20/12 ,  C22F1/18 ,  B23K31/02 ,  B23K20/00 ,  C22F1/10 ,  F01D5/18 ,  B23K31/12

CPC classification number: F01D5/3061 ,  B23K20/002 ,  B23K20/1205 ,  B23K31/02 ,  B23K31/12 ,  B23P15/006 ,  C22F1/10 ,  C22F1/183 ,  F01D5/187 ,  F01D5/28 ,  F01D5/288 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/239 ,  F05D2230/411 ,  F05D2230/90 ,  F05D2240/30 ,  F05D2260/20 ,  F05D2260/941 ,  F05D2300/17 ,  F05D2300/174

Abstract: Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A hybrid bonded turbine rotor comprises a turbine disk and a plurality of turbine blades each metallurgically bonded to a corresponding raised blade attachment surface of a plurality of raised blade attachment surfaces of the turbine disk to define a bond plane located at a selected radial position. Turbine disk has a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with the plurality of raised blade attachment surfaces defining the outer periphery. The selected radial position is outboard of the live rim. Each pair of adjacent turbine blades defines a shank cavity therebetween. The shank cavity extends radially outwardly from the live rim and includes a live rim notch disposed below the bond plane and above the live rim.

Abstract translation: 提供混合式涡轮转子及其制造方法。 混合结合的涡轮机转子包括涡轮盘和多个涡轮机叶片，每个涡轮机叶片各自冶金地结合到涡轮盘的多个凸起的叶片附接表面的对应的凸起的叶片附接表面，以限定位于选定径向位置处的接合平面。 涡轮盘具有边缘部分，其包括周向连续材料的活边缘和在涡轮盘的外周中的多个带状轮缘切口，与限定外周的多个凸起刀片附接表面交替。 所选的径向位置是活动边缘的外侧。 每对相邻的涡轮叶片在它们之间限定一个柄腔。 柄腔从活边缘径向向外延伸，并且包括设置在接合平面下方和活边缘上方的活边缘凹口。

公开(公告)号：US10900363B2

公开(公告)日：2021-01-26

申请号：US16051560

申请日：2018-08-01

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Brent Ludwig ,  Don Mittendorf ,  David R. Waldman ,  Malak Fouad Malak

IPC: F01D5/28 ,  B23P15/02

Abstract: Cladding material is applied by laser to a net-shape. A method of cladding a host component includes installing the component in a fixture. A shroud component is located against the host component adjacent a select location for the cladding. Cladding is applied to the host component to the select location and adjacent to shroud component so that the shroud component defines an edge of the cladding as applied. The edge of the cladding as defined by the shroud component defines a desired cladding profile requiring no/approximately no post-cladding processing to remove over-cladded material.

公开(公告)号：US10857596B1

公开(公告)日：2020-12-08

申请号：US16127383

申请日：2018-09-11

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Don Mittendorf ,  Jason Smoke ,  Brent Ludwig

IPC: B22F5/04 ,  F01D5/20 ,  B22F3/15 ,  B23P15/04 ,  B29C43/10

Abstract: A method of producing an abrasive tip for a turbine blade includes producing or obtaining a metal powder that is mixed with an abrasive ceramic powder and producing or obtaining a metallic mold that is in the shape of an airfoil. The metallic mold includes a hollow interior portion. The method further includes sealing the metal and ceramic powder mixture within the hollow interior portion of the metallic mold under vacuum and subjecting the sealed mold to a hot isostatic pressing process. The hot isostatic pressing process compacts and binds the metal and ceramic powder mixture together into a solid article in the shape of the airfoil. Still further, the method includes slicing the solid article into a plurality of airfoil-shaped slices and bonding one slice of the plurality of airfoil-shaped slices to a tip portion of a turbine blade.

公开(公告)号：US20200360998A1

公开(公告)日：2020-11-19

申请号：US16127383

申请日：2018-09-11

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Don Mittendorf ,  Jason Smoke ,  Brent Ludwig

IPC: B22F5/04 ,  B22F7/08 ,  B22F3/15 ,  B22F3/24

Abstract: A method of producing an abrasive tip for a turbine blade includes producing or obtaining a metal powder that is mixed with an abrasive ceramic powder and producing or obtaining a metallic mold that is in the shape of an airfoil. The metallic mold includes a hollow interior portion. The method further includes sealing the metal and ceramic powder mixture within the hollow interior portion of the metallic mold under vacuum and subjecting the sealed mold to a hot isostatic pressing process. The hot isostatic pressing process compacts and binds the metal and ceramic powder mixture together into a solid article in the shape of the airfoil. Still further, the method includes slicing the solid article into a plurality of airfoil-shaped slices and bonding one slice of the plurality of airfoil-shaped slices to a tip portion of a turbine blade.

公开(公告)号：US10036254B2

公开(公告)日：2018-07-31

申请号：US14939360

申请日：2015-11-12

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  David K. Jan ,  Don Mittendorf ,  Brent Ludwig ,  Amandine Miner ,  Deanna Pinar Chase

IPC: B23K20/02 ,  F01D5/30 ,  F01D5/04 ,  F01D5/28 ,  F01D5/34 ,  B23K101/00

CPC classification number: F01D5/048 ,  B23K20/021 ,  B23K2101/001 ,  B23P15/006 ,  F01D5/28 ,  F01D5/3061 ,  F01D5/34 ,  F05D2230/42 ,  F05D2300/175 ,  F05D2300/607 ,  F05D2300/609

Abstract: Dual alloy bladed rotors are provided, as are methods for manufacturing dual alloy bladed rotors. In one embodiment, the method includes arranging bladed pieces in a ring formation such that contiguous bladed pieces contact along shank-to-shank bonding interfaces. The ring formation is positioned around a hub disk, which is contacted by the bladed pieces along a shank-to-hub bonding interface. A metallic sealing material is deposited between contiguous bladed pieces utilizing, for example, a laser welding process to produce an annular seal around the ring formation. A hermetic cavity is then formed, which is circumferentially bounded by the annular seal and which encloses the shank-to-shank and shank-to-hub bonding interface. Afterwards, a Hot Isostatic Pressing process is performed during which the ring formation and the hub disk are exposed to elevated pressures external to the hermetic cavity sufficient to diffusion bond the shank-to-shank and shank-to-hub bonding interface.

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

IPC: F01D5/18 ,  F01D5/14 ,  B22F5/04 ,  B22F3/105 ,  B22F5/00 ,  B22F7/00

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.

公开(公告)号：US20180036796A1

公开(公告)日：2018-02-08

申请号：US15231377

申请日：2016-08-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Don Mittendorf ,  Tho X. Bui ,  Will Otaluka ,  Edwin Martinez ,  John Woodward ,  Yathiraj Kasal

IPC: B22D27/04 ,  B33Y30/00 ,  B33Y40/00 ,  C30B29/52 ,  B05D3/02 ,  B05D7/14 ,  B22F3/00 ,  C30B11/00 ,  B33Y10/00 ,  B05D1/18

CPC classification number: B22D27/045 ,  B05D1/18 ,  B05D3/0254 ,  B05D7/14 ,  B22F3/008 ,  B22F3/1055 ,  B22F3/24 ,  B22F5/009 ,  B22F5/04 ,  B22F2998/10 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y40/00 ,  C30B11/002 ,  C30B11/003 ,  C30B29/52 ,  Y02P10/295 ,  B22F2003/248 ,  B22F2003/247 ,  B22F5/003

Abstract: A method of manufacturing a directionally solidified article of the present disclosure includes providing a collection of particulate material and additively manufacturing a first article with an outer wall from the particulate material. The outer wall defines at least part of a cavity. The cavity contains an amount of the particulate material. The method also includes encasing at least a portion of the first article with an outer member. The outer member defines an internal cavity that corresponds to the first article. The method further includes heating the outer member and the first article to melt the first article into a molten mass within the internal cavity of the outer member. Additionally, the method includes solidifying the molten mass along a predetermined solidification path within the outer member to form a second article that corresponds to at least a portion of the internal cavity of the outer member.

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

IPC: F01D9/04 ,  F01D1/04 ,  B23P11/00

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.

公开(公告)号：US20170022827A1

公开(公告)日：2017-01-26

申请号：US14806933

申请日：2015-07-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： David R. Waldman ,  Don Mittendorf ,  Mark C. Morris ,  Michael Vinup

IPC: F01D5/30 ,  B23K20/12 ,  B23K20/22 ,  B23K20/02 ,  B23K20/14 ,  B23K20/08 ,  B23K9/167 ,  B23K9/23 ,  B23K5/14 ,  B23K5/00 ,  B23K10/02 ,  B23K15/00 ,  B23K26/32 ,  B23K26/21 ,  F01D5/02

CPC classification number: F01D5/3061 ,  B23K20/1205 ,  B23K20/16 ,  B23K2101/001 ,  F01D5/082 ,  F01D5/34 ,  F01D11/006 ,  F05D2230/239 ,  F05D2300/606 ,  F05D2300/607 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A method for manufacturing a hybrid bonded turbine rotor comprises the steps of providing turbine disk having a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with a plurality of raised blade attachment surfaces defining the outer periphery; providing a plurality of turbine blades, each of which comprising an airfoil portion and a shank portion, the shank portion having a base surface; metallurgically bonding a compliant alloy material layer to either or both of the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks; and linear friction welding the plurality of blades to the turbine disk so as to form a bond plane between the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks, the compliant alloy material layer being disposed at the bond plane.

Abstract translation: 提供混合式涡轮转子及其制造方法。 一种混合式混合涡轮机转子的制造方法，包括以下步骤：提供涡轮盘，该涡轮盘具有边缘部分，该边缘部分包括周向连续材料的活边缘和在涡轮盘的外周中的多个带状轮缘切口， 限定外周的附接表面; 提供多个涡轮叶片，每个涡轮叶片包括翼型部分和柄部分，所述柄部分具有基部表面; 将柔性合金材料层冶金结合到涡轮盘的凸起刀片附件表面中的一个或两个以及刀片柄的基座表面; 并且将所述多个叶片线性摩擦焊接到所述涡轮盘，以便在所述涡轮盘的所述凸起的叶片附接表面与所述叶片柄的基底表面之间形成接合平面，所述柔性合金材料层设置在所述接合平面处。

公开(公告)号：US20150354379A1

公开(公告)日：2015-12-10

申请号：US14297406

申请日：2014-06-05

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Amandine Miner ,  David K. Jan ,  Don Mittendorf ,  Jason Smoke

IPC: F01D5/30 ,  B23K1/00 ,  B23K31/02 ,  B23K20/02 ,  B23K20/00

CPC classification number: B23K20/028 ,  B23K1/00 ,  B23K1/0018 ,  B23K20/002 ,  B23K20/021 ,  B23K20/023 ,  B23K20/14 ,  B23K20/22 ,  B23K20/26 ,  B23K31/02 ,  B23K2101/001 ,  B23P15/006 ,  F01D5/3061 ,  F01D5/34 ,  F05D2220/323 ,  F05D2230/236 ,  F05D2230/60 ,  F05D2300/17 ,  F05D2300/606 ,  F05D2300/607 ,  Y10T29/49323

Abstract: Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.

Abstract translation: 提供双合金涡轮转子及其制造方法。 双合金涡轮转子包括组装的叶片环和结合到组装的叶片环的轮毂。 组装的叶片环包括选自单晶合金，定向凝固合金或等轴合金的第一合金。 轮毂包括第二合金。 该方法包括将轮毂定位在叶片环内以限定轮毂和叶片环之间的界面。 该接口是非接触式界面或接触界面。 接口由一对隔膜包围。 界面被真空密封。 在真空密封步骤之后，叶片环结合到轮毂上。