公开(公告)号：US20220356840A1

公开(公告)日：2022-11-10

申请号：US17313605

申请日：2021-05-06

Applicant: Raytheon Technologies Corporation

Inventor： Paul R. Hanrahan ,  Daniel Bernard Kupratis ,  Christopher J. Hanlon

IPC: F02C7/052

Abstract: A gas turbine engine includes a core section including a compressor, a main combustor, and a main turbine. Combustion products from the main combustor drive rotation of the turbine and the compressor. A power turbine is fluidly connected to the main turbine and driven by exhaust from the main turbine. The gas turbine engine further includes a fan section having a fan rotor located fluidly upstream of the core section. The power turbine is operably connected to the fan rotor to drive rotation of the fan rotor via rotation of the power turbine. The gas turbine engine includes a bleed arrangement having one or more bleed passages configured to divert a bleed airflow from the compressor around the main combustor and main turbine, and reintroduce the bleed airflow into the power turbine.

公开(公告)号：US20220349341A1

公开(公告)日：2022-11-03

申请号：US17864982

申请日：2022-07-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan ,  Arthur M. Salve, JR.

IPC: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10

Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.

公开(公告)号：US20210404480A1

公开(公告)日：2021-12-30

申请号：US16913019

申请日：2020-06-26

Applicant: Raytheon Technologies Corporation

Inventor： Todd A. Davis ,  Paul R. Hanrahan

IPC: F04D29/059 ,  F16C19/36 ,  F16C33/58 ,  F16C35/073

Abstract: A bearing assembly of a gas turbine engine includes a bearing inner race, a bearing outer race located radially outboard of the bearing inner race and a plurality of bearing elements located between the bearing inner race and the bearing outer race. A centering spring is operably connected to and supports the bearing outer race. The centering spring is an annular structure including a base portion, a tip portion, and a plurality of beams extending axially between the base portion and the tip portion.

公开(公告)号：US20210381431A1

公开(公告)日：2021-12-09

申请号：US16891492

申请日：2020-06-03

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan

IPC: F02C3/107 ,  F02C9/18 ,  F01D9/06 ,  F01D13/00 ,  F01D25/16 ,  F01D17/16

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. A row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths. A method of operation for a gas turbine engine is also disclosed.

公开(公告)号：US11193425B2

公开(公告)日：2021-12-07

申请号：US16445469

申请日：2019-06-19

Applicant: Raytheon Technologies Corporation

Inventor： Paul R. Hanrahan ,  Arthur M. Salve, Jr. ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02C7/32 ,  F02C6/08

Abstract: A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.