David B Riddle

US Patent:

20180128206, May 10, 2018

Filed:

Nov 9, 2016

Appl. No.:

15/347301

Inventors:

- Schenectady NY, US
David Baker Riddle - Cincinnati OH, US
Alan Roy Stuart - Cincinnati OH, US
Jeffrey Donald Clements - Mason OH, US

International Classification:

F02K 1/72

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.

US Patent:

20170106991, Apr 20, 2017

Filed:

Oct 19, 2015

Appl. No.:

14/886262

Inventors:

- Schenectady NY, US
Richard David Cedar - Cincinnati OH, US
David Baker Riddle - Cincinnati OH, US

International Classification:

B64D 33/02
F01D 25/24
F01D 5/02

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.