公开(公告)号：US11053843B2

公开(公告)日：2021-07-06

申请号：US16158545

申请日：2018-10-12

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02C3/107 ,  F01D25/16 ,  F02K3/06

Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.

公开(公告)号：US20210062724A1

公开(公告)日：2021-03-04

申请号：US17037916

申请日：2020-09-30

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D1/26 ,  F01D15/12

Abstract: A turbofan gas turbine engine includes a fan section having a fan, a compressor section including a low pressure compressor and a high pressure compressor, a geared architecture including an epicyclic gear train, a turbine section including a low pressure turbine and a high pressure turbine, the fan driven by the low pressure turbine through the geared architecture, and a power density between 4.84 lbf/in3 and 5.5 lbf/in3.

公开(公告)号：US10934934B2

公开(公告)日：2021-03-02

申请号：US16143684

申请日：2018-09-27

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Francis R. Moon

IPC: F02C7/36 ,  F02C6/02 ,  F02C3/10 ,  F02C3/14 ,  F02C3/05 ,  F02K3/06 ,  F01D17/14 ,  F02K3/075 ,  F02C3/13 ,  F02C9/18 ,  F02K3/065 ,  F02C3/107

Abstract: A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed.