公开(公告)号：US10167088B2

公开(公告)日：2019-01-01

申请号：US14886262

申请日：2015-10-19

Applicant: General Electric Company

Inventor： Adam Wayne Clark ,  Richard David Cedar ,  David Baker Riddle

IPC: F01D5/02 ,  B64D33/02 ,  F01D25/24 ,  F02C7/04 ,  B64C11/14

Abstract: Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8. Aft spinner section may be substantially tangential to platform leading edges of platforms of fan blades. Aft spinner section may have cambered or an elliptical axially curved cross-section.Spinner axial cross-section may have longer spinner axial distance compared to baseline axial distance of baseline cross-section and spinner aspect ratio greater than baseline aspect ratio of baseline cross-section.

公开(公告)号：US20170106991A1

公开(公告)日：2017-04-20

申请号：US14886262

申请日：2015-10-19

Applicant: General Electric Company

Inventor： Adam Wayne Clark ,  Richard David Cedar ,  David Baker Riddle

IPC: B64D33/02 ,  F01D25/24 ,  F01D5/02

CPC classification number: B64D33/02 ,  B64C11/14 ,  B64D2033/0286 ,  F01D5/02 ,  F01D25/24 ,  F02C7/04 ,  F05D2220/323 ,  F05D2240/20 ,  F05D2250/232 ,  F05D2250/51 ,  Y02T50/671

Abstract: Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8. Aft spinner section may be substantially tangential to platform leading edges of platforms of fan blades. Aft spinner section may have cambered or an elliptical axially curved cross-section. Spinner axial cross-section may have longer spinner axial distance compared to baseline axial distance of baseline cross-section and spinner aspect ratio greater than baseline aspect ratio of baseline cross-section.

公开(公告)号：US20230021836A1

公开(公告)日：2023-01-26

申请号：US17382467

申请日：2021-07-22

Applicant: General Electric Company

Inventor： David Baker Riddle ,  Keith Edward James Blodgett ,  Timothy Richard DePuy ,  William Joseph Bowden

IPC: B64D27/12

Abstract: An aircraft includes a fuselage, a wing connected to and extending outward from the fuselage, and an engine mounted to the wing. The engine includes turbomachine defining a centerline axis, a fan, and an exhaust section with an outlet nozzle. The turbomachine defines a centerline axis. The fan is connected to and is disposed upstream from the turbomachine. The fan is disposed to rotate about the centerline axis. During operation of the engine, an exhaust stream is expelled from the outlet nozzle of the exhaust section. The exhaust stream defines a mean direction of flow in the downstream direction from the exhaust section. The mean direction of flow defines a first angle with the centerline axis of the turbomachine that is greater than zero such that the centerline axis is oriented downwardly along the vertical direction relative to the mean direction of flow of the exhaust stream.

公开(公告)号：US20180128206A1

公开(公告)日：2018-05-10

申请号：US15347301

申请日：2016-11-09

Applicant: General Electric Company

Inventor： Richard David Cedar ,  David Baker Riddle ,  Alan Roy Stuart ,  Jeffrey Donald Clements

IPC: F02K1/72

CPC classification number: F02K1/72 ,  F02K3/06 ,  F05D2220/327 ,  F05D2260/904 ,  Y02T50/671

Abstract: A turbofan engine is provided having a fan and a nacelle assembly enclosing the fan. The nacelle assembly includes a thrust reverser system having one or more cascade segments configured to translate at least partially along an axial direction of the turbofan engine. The turbofan engine further includes a core operable with the fan and at least partially enclosed by the nacelle. The core includes a turbine section having a low pressure turbine defining an exit diameter. A ratio of the exit diameter of the low pressure turbine to a fan diameter of the fan is less than 0.5, providing for a more compact turbofan engine.