公开(公告)号：US11970974B2

公开(公告)日：2024-04-30

申请号：US17570764

申请日：2022-01-07

Applicant: Raytheon Technologies Corporation

Inventor： Robert E. Malecki ,  Andrew Hahn ,  Marc J. Muldoon ,  Jesse M. Chandler ,  Joseph B. Staubach

IPC: F02C7/20 ,  B64C7/02 ,  B64D27/12 ,  B64D29/06 ,  B64D29/08 ,  F02C7/06 ,  F02C7/14 ,  F02C7/32

CPC classification number: F02C7/20 ,  B64C7/02 ,  B64D27/12 ,  B64D29/06 ,  B64D29/08 ,  F02C7/06 ,  F02C7/14 ,  F02C7/32 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2260/213 ,  F05D2260/4031 ,  F05D2260/98

Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.

公开(公告)号：US20220136441A1

公开(公告)日：2022-05-05

申请号：US17570764

申请日：2022-01-07

Applicant: Raytheon Technologies Corporation

Inventor： Robert E. Malecki ,  Andrew Hahn ,  Marc J. Muldoon ,  Jesse M. Chandler ,  Joseph B. Staubach

IPC: F02C7/20 ,  B64C7/02 ,  B64D29/08 ,  F02C7/32 ,  F02C7/06 ,  B64D29/06 ,  B64D27/12 ,  F02C7/14

Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.

公开(公告)号：US20220010689A1

公开(公告)日：2022-01-13

申请号：US17482666

申请日：2021-09-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

IPC: F01D25/24 ,  F02K3/06 ,  F01D5/14 ,  F02C7/04 ,  F01D5/02 ,  F01D15/12 ,  F01D17/10

Abstract: A gas turbine engine assembly may include, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L between the first reference plane and the second reference plane. A dimensional relationship of L/D may be between 0.30 and 0.40.

公开(公告)号：US20210285403A1

公开(公告)日：2021-09-16

申请号：US17198651

申请日：2021-03-11

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

IPC: F02K3/068 ,  F01D25/24 ,  F02C7/04

Abstract: A gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a length of the inlet portion having a dimension L, and a dimensional relationship of L/D between 0.30 and 0.40.

公开(公告)号：US11236701B2

公开(公告)日：2022-02-01

申请号：US16031202

申请日：2018-07-10

Applicant: Raytheon Technologies Corporation

Inventor： Dmitriy B. Sidelkovskiy ,  Oleg Petrenko ,  Robert E. Malecki ,  Steven H. Zysman

IPC: F02K1/78 ,  B64D29/00 ,  F02K1/40 ,  F02K1/52 ,  F02K1/00 ,  F02K1/82 ,  F02K1/36 ,  F02K3/077 ,  F02C3/04 ,  F02K3/06 ,  B64D29/02 ,  B64D29/04

Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.

公开(公告)号：US11781505B2

公开(公告)日：2023-10-10

申请号：US17198651

申请日：2021-03-11

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

IPC: F02K3/068 ,  F01D25/24 ,  F02C7/04

CPC classification number: F02K3/068 ,  F01D25/24 ,  F02C7/04 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/60

Abstract: A gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a length of the inlet portion having a dimension L, and a dimensional relationship of L/D between 0.30 and 0.40.

公开(公告)号：US11781447B2

公开(公告)日：2023-10-10

申请号：US17482666

申请日：2021-09-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Wesley K. Lord ,  Robert E. Malecki ,  Yuan J. Qiu ,  Becky E. Rose ,  Jonathan Gilson

IPC: F01D25/24 ,  F02K3/06 ,  F01D5/14 ,  F02C7/04 ,  F01D5/02 ,  F01D15/12 ,  F01D17/10

CPC classification number: F01D25/24 ,  F01D5/02 ,  F01D5/141 ,  F01D15/12 ,  F01D17/105 ,  F02C7/04 ,  F02K3/06 ,  F05D2220/32 ,  F05D2250/00 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/60

Abstract: A gas turbine engine assembly may include, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L between the first reference plane and the second reference plane. A dimensional relationship of L/D may be between 0.30 and 0.40.

公开(公告)号：US20220136440A1

公开(公告)日：2022-05-05

申请号：US17085184

申请日：2020-10-30

Applicant: Raytheon Technologies Corporation

Inventor： Robert E. Malecki ,  Andrew Hahn ,  Marc J. Muldoon ,  Jesse M. Chandler ,  Joseph B. Staubach

IPC: F02C7/20 ,  F02C7/32 ,  F02C7/14 ,  B64D29/08 ,  B64D27/12 ,  F02C7/06

Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.