公开(公告)号：US11725670B2

公开(公告)日：2023-08-15

申请号：US17892529

申请日：2022-08-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F04D29/54 ,  F04D29/68 ,  F02K3/04 ,  F04D29/52 ,  F04D19/02 ,  F04D25/04 ,  F04D29/32 ,  F04D29/56

CPC classification number: F04D29/547 ,  F02K3/04 ,  F02K3/06 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/681 ,  F05D2220/3217 ,  F05D2220/36 ,  F05D2260/606

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US11428242B2

公开(公告)日：2022-08-30

申请号：US16715528

申请日：2019-12-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F04D29/54 ,  F04D29/68 ,  F02K3/04 ,  F04D29/52 ,  F04D19/02 ,  F04D25/04 ,  F04D29/32 ,  F04D29/56

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

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：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：US11680531B2

公开(公告)日：2023-06-20

申请号：US17682313

申请日：2022-02-28

Applicant: Raytheon Technologies Corporation

Inventor： Christopher J. Hanlon ,  James F. Krenzer ,  Becky E. Rose ,  Mark F. Zelesky

IPC: F02C9/18 ,  F02C6/08 ,  F02C7/052 ,  F02C7/057 ,  F02C9/44 ,  F02K3/075 ,  F04D27/02

CPC classification number: F02C9/18 ,  F02C6/08 ,  F02C7/052 ,  F02C7/057 ,  F02C9/44 ,  F02K3/075 ,  F04D27/0215 ,  F05D2260/606 ,  F05D2260/607

Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.

公开(公告)号：US20230332622A1

公开(公告)日：2023-10-19

申请号：US18207805

申请日：2023-06-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F04D25/04 ,  F04D29/32 ,  F04D29/68 ,  F04D29/54 ,  F04D29/52 ,  F04D19/02 ,  F04D29/56 ,  F02K3/04

CPC classification number: F04D29/547 ,  F02K3/04 ,  F02K3/06 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/681 ,  F05D2220/3217 ,  F05D2220/36 ,  F05D2260/606

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor that delivers flow to a core flowpath and a compressor section including first and second compressors. The core flowpath passes through the first compressor. The core flowpath in the first compressor has an outer diameter relative to the engine longitudinal axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US20230315938A1

公开(公告)日：2023-10-05

申请号：US17963898

申请日：2022-10-11

Applicant: Raytheon Technologies Corporation

Inventor： Anil Prasad ,  Becky E. Rose ,  Lawrence P. Roberts ,  Uyen Phan

IPC: G06F30/20

CPC classification number: G06F30/20

Abstract: A method is providing comprising receiving, via a processor, a digital representation of a potentially repaired blade from an inspection system, the digital representation including a repair blend profile, the digital representation based on an inspected blade of an inspected bladed rotor; generating, via the processor, an airfoil definition file corresponding to the digital representation, inputting, via the processor, the airfoil definition file into an aerodynamic simulator, receiving, via the processor, simulation results from the aerodynamic simulator of the potentially repaired blade; analyzing, via the processor, an overall engine impact of the potentially repaired blade based on the simulation results, inputting, via the processor, a plurality of simulation results into an aerodynamic effect translator, and receiving, via the processor, a translated impact for local effect of a repaired bladed rotor with the potentially repaired blade.

公开(公告)号：US20230131276A1

公开(公告)日：2023-04-27

申请号：US17892529

申请日：2022-08-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F04D29/54 ,  F04D29/68 ,  F02K3/04 ,  F04D29/52 ,  F04D19/02 ,  F02K3/06 ,  F04D25/04 ,  F04D29/32 ,  F04D29/56

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.