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：US20230025200A1

公开(公告)日：2023-01-26

申请号：US17958405

申请日：2022-10-02

Applicant: Raytheon Technologies Corporation

Inventor： Yuan J. Qiu ,  Robert M. Miller ,  Wesley K. Lord ,  Gavin Hendricks

IPC: F02C7/04 ,  F02K3/06 ,  F01D5/02 ,  F01D17/10 ,  F01D25/24 ,  F02C3/04

Abstract: A gas turbine engine includes a fan section including a fan. A fan nacelle surrounds the fan and includes an inlet with an inlet leading edge plane and a throat. A compressor section is arranged in a core nacelle and includes a first compressor and a second compressor. A turbine section is arranged in the core nacelle and includes a fan drive turbine and a second turbine. A fan hub mounts the fan and a spinner axially forward of the fan. The fan drive turbine drives the fan through a geared architecture. The fan includes a fan leading edge forward-most point spaced apart from the inlet leading edge plane by an inlet length. The spinner includes a spinner length from a spinner forward-most point to the fan leading edge forward-most point. A ratio of the spinner length to inlet length is greater than or equal to 0.5.