公开(公告)号：US20190061961A1

公开(公告)日：2019-02-28

申请号：US15682862

申请日：2017-08-22

Applicant: General Electric Company

Inventor： Nikolai N. Pastouchenko ,  Jixian Yao, JR. ,  Narendra Joshi

IPC: B64D27/08 ,  B64D27/24 ,  B64D29/04 ,  F01D7/00

Abstract: An aircraft propulsion system includes a boundary layer ingestion (BLI) fan system disposed at an aft end of an aircraft. The BLI fan system includes a fan that is configured to rotate about an axial centerline of the BLI fan system in a first direction of rotation. The BLI fan system includes blades that are positioned at a first pitch angle configured to rotate with the fan. An electric motor operably coupled with the BLI fan system is configured to change a direction of rotation of the fan to a different, second direction of rotation. An actuator operably coupled with the BLI fan system is configured to change a position of the blades of the fan to be positioned at a different, second pitch angle.

公开(公告)号：US20180179951A1

公开(公告)日：2018-06-28

申请号：US15390112

申请日：2016-12-23

Applicant: General Electric Company

Inventor： Venkat Eswarlu Tangirala ,  Keith Robert McManus ,  Michael Bowman ,  Narendra Joshi ,  Joel Haynes ,  Anthony Dean

IPC: F02C3/16 ,  F02C3/04 ,  F02C3/34

CPC classification number: F02C3/16 ,  F02C3/34 ,  F02C5/02 ,  F23R2900/03341

Abstract: A turbine engine includes at least one compressor configured to increase pressure of a fluid flow and a primary combustor coupled in flow communication with the at least one compressor. The primary combustor is configured to receive pressurized fluid flow from the at least one compressor. The primary combustor includes a housing defining at least one combustion chamber. The primary combustor is configured for a rotating detonation process to occur within said at least one combustion chamber. The turbine engine also includes at least one supplemental combustor coupled in flow communication with the primary combustor. The at least one supplemental combustor is configured to receive combustion products and perform a combustion operation. The turbine engine further includes a turbine assembly coupled in flow communication with the at least one supplemental combustor. The turbine assembly is configured to receive combustion products from the at least one supplemental combustor.