公开(公告)号：US20160201514A1

公开(公告)日：2016-07-14

申请号：US14853530

申请日：2015-09-14

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  John T. Ols

IPC: F01D25/24 ,  F01D25/00 ,  F01D5/06 ,  F01D9/04

CPC classification number: F01D25/246 ,  B23P6/002 ,  F01D9/041 ,  F05D2230/30 ,  F05D2230/60 ,  F05D2230/64 ,  F05D2230/70 ,  F05D2230/80 ,  Y10T29/49318 ,  Y10T29/49872

Abstract: A gas-turbine engine is provided comprising a high-pressure turbine, a low-pressure turbine aft of the high-pressure turbine, and a housing around the low-pressure turbine and the high-pressure turbine. A stator may be disposed between the low-pressure turbine and the high-pressure turbine with a boss formed on the stator. A bushing may be retained in the boss with a pin coupled to the housing and partially within the bushing. A method of mounting a full-ring stator is also provided, the method including the steps of inserting a bushing into a boss of the full-ring stator by press fitting, and inserting a pin into the bushing of the full-ring stator.

Abstract translation: 提供一种燃气涡轮发动机，其包括高压涡轮机，高压涡轮机的低压涡轮机后部和围绕低压涡轮机和高压涡轮机的壳体。 定子可以设置在低压涡轮机和高压涡轮机之间，并具有形成在定子上的凸台。 衬套可以被保持在凸台中，销具有联接到壳体并且部分地在衬套内的销。 还提供了一种安装全环定子的方法，该方法包括以下步骤：通过压配合将衬套插入全环定子的凸台中，并将销插入全环定子的衬套中。

公开(公告)号：US20210222878A1

公开(公告)日：2021-07-22

申请号：US16746210

申请日：2020-01-17

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Caroline Karanian ,  John T. Ols

IPC: F23R3/00

Abstract: A gas turbine engine includes a turbine section including a first vane stage. The gas turbine engine further includes a combustor disposed forward of the first vane stage. The combustor includes a combustion chamber in fluid communication with the first vane stage. The combustion chamber is radially defined between a first shell and a second shell. The first shell includes a first seal assembly at an aft end of the first shell. The first seal assembly includes a conformal seal forming a first seal between the first shell and a forward face of the first vane stage. The second shell includes a second seal assembly at an aft end of the second shell. The second seal assembly includes a brush seal forming a second seal between the second shell and the forward face of the first vane stage.

公开(公告)号：US11021976B2

公开(公告)日：2021-06-01

申请号：US14862351

申请日：2015-09-23

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  John T. Ols ,  Kyle C. Lana

IPC: F01D9/02 ,  F01D1/04 ,  F01D11/00 ,  F01D5/08

Abstract: A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft of the high pressure turbine and proximate a cavity defined by the aft blade platform. A vane of the static structure may have a vane platform with a shaped tip extending into the cavity.

公开(公告)号：US20200024995A1

公开(公告)日：2020-01-23

申请号：US16391544

申请日：2019-04-23

Applicant: United Technologies Corporation

Inventor： John T. Ols ,  Steven D. Porter

IPC: F01D9/04 ,  F01D11/00 ,  F01D11/02 ,  F01D25/16

Abstract: A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.

公开(公告)号：US10328526B2

公开(公告)日：2019-06-25

申请号：US15026410

申请日：2014-10-24

Applicant: United Technologies Corporation

Inventor： John T. Ols ,  Wangen Lin ,  Giovanni Whitman

IPC: B23K26/34 ,  B23K26/342 ,  B23K35/30 ,  B23K35/02 ,  B23P6/00 ,  F01D5/00 ,  B23K26/323 ,  B22F5/00 ,  B22F7/06 ,  B23K26/144 ,  F01D9/04 ,  F01D25/24 ,  C22F1/10 ,  B23K101/00 ,  B23K103/18

Abstract: A method is provided for reworking a component. The method includes at least partially filling a cavity in a non-fusion weldable base alloy with a multiple of layers of a multiple of laser powder deposition spots formed of a filler alloy. Each of the multiple of laser powder deposition spots at least partially overlaps at least one of another of the multiple of laser powder deposition spots. The filler alloy may be different than the non-fusion weldable base alloy.

公开(公告)号：US09982548B2

公开(公告)日：2018-05-29

申请号：US14890496

申请日：2014-06-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Ols ,  Karl A. Mentz ,  Richard N. Allen ,  Steven D. Porter ,  Renee J. Jurek ,  Paul K. Sanchez ,  Sandra S. Pinero

IPC: F01D9/04 ,  F01D5/14 ,  F01D5/02 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/143 ,  F01D9/04 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/80 ,  F05D2250/71 ,  F05D2250/90 ,  Y02T50/673

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

公开(公告)号：US10408088B2

公开(公告)日：2019-09-10

申请号：US14853530

申请日：2015-09-14

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  John T. Ols

IPC: F01D25/24 ,  F01D9/04 ,  B23P6/00

Abstract: A gas-turbine engine is provided comprising a high-pressure turbine, a low-pressure turbine aft of the high-pressure turbine, and a housing around the low-pressure turbine and the high-pressure turbine. A stator may be disposed between the low-pressure turbine and the high-pressure turbine with a boss formed on the stator. A bushing may be retained in the boss with a pin coupled to the housing and partially within the bushing. A method of mounting a full-ring stator is also provided, the method including the steps of inserting a bushing into a boss of the full-ring stator by press fitting, and inserting a pin into the bushing of the full-ring stator.

公开(公告)号：US09945236B2

公开(公告)日：2018-04-17

申请号：US14893229

申请日：2014-05-22

Applicant: United Technologies Corporation

Inventor： Steven W. Burd ,  Meggan Harris ,  John T. Ols ,  William G. Askey

IPC: F01D9/04 ,  F01D5/30 ,  F01D5/34 ,  B22D25/02 ,  F01D5/02 ,  F01D5/12 ,  F01D25/24 ,  F01D25/30 ,  B23P15/00

CPC classification number: F01D5/3069 ,  B22D25/02 ,  B23P15/006 ,  F01D5/02 ,  F01D5/12 ,  F01D5/3023 ,  F01D5/3061 ,  F01D5/34 ,  F01D9/044 ,  F01D25/24 ,  F01D25/30 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/232 ,  F05D2230/25 ,  F05D2230/60 ,  F05D2240/24

Abstract: A unitary one-piece hub has first and second rings and a midsection arranged between the first and second rings. The midsection includes a plurality of windows configured to receive a plurality of cross members. The windows include a lip configured to surround the cross members. A gas turbine engine and a method of providing a hub for a gas turbine engine are also disclosed.

公开(公告)号：US20160236298A1

公开(公告)日：2016-08-18

申请号：US15026410

申请日：2014-10-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Ols ,  Wangen Lin ,  Giovanni Whitman

IPC: B23K26/342 ,  F01D9/04 ,  F01D25/24 ,  B23K26/00 ,  B23K26/144

CPC classification number: B23K26/342 ,  B22F5/009 ,  B22F7/062 ,  B22F2007/068 ,  B22F2999/00 ,  B23K26/144 ,  B23K26/323 ,  B23K35/0244 ,  B23K35/3033 ,  B23K2101/001 ,  B23K2103/26 ,  B23P6/007 ,  C22F1/10 ,  F01D5/005 ,  F01D9/041 ,  F01D25/246 ,  F05D2220/32 ,  F05D2230/234 ,  F05D2230/31 ,  F05D2230/42 ,  F05D2300/175 ,  F05D2300/177 ,  B22F3/105

Abstract: A method is provided for reworking a component. The method includes at least partially filling a cavity in a non-fusion weldable base alloy with a multiple of layers of a multiple of laser powder deposition spots formed of a filler alloy. Each of the multiple of laser powder deposition spots at least partially overlaps at least one of another of the multiple of laser powder deposition spots. The filler alloy may be different than the non-fusion weldable base alloy.

Abstract translation: 提供了一种用于重新组装组件的方法。 该方法包括至少部分地填充由非填充合金形成的多个激光粉末沉积点的多个层的不可焊接的基础合金中的空腔。 多个激光粉末沉积点中的每一个至少部分地与多个激光粉末沉积点中的至少一个重叠。 填充合金可以不同于不熔焊基体合金。

公开(公告)号：US20160069200A1

公开(公告)日：2016-03-10

申请号：US14787332

申请日：2014-05-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Ols ,  Richard N. Allen ,  Steven D. Porter ,  Paul K. Sanchez ,  Sandra S. Pinero

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/042 ,  F01D5/14 ,  F01D5/141 ,  F01D9/02 ,  F01D9/04 ,  F01D9/047 ,  F01D25/24 ,  F05D2230/53 ,  Y02T50/671 ,  Y02T50/673

Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.

Abstract translation: 叶片具有在径向外平台和径向内平台之间延伸的翼型件。 至少一个平台具有标称径向较薄的部分，以及限定径向较厚部分的垫。 垫的径向厚度大于标称径向较薄部分的厚度。 垫片围绕在径向外平台的一侧的翼型件的外周边。 垫具有变化的径向厚度。 还公开了中涡轮机架和燃气涡轮发动机。