Patent · US Active

Aircraft gas turbine with variable bypass nozzle by deforming element

US8850824B2 · kind B2 · utility

0Cited by

4References

10Claims

0Family size

Assignee

ROLLS-ROYCE DEUTSCHLAND LTD & CO KG · DE

Inventors

Predrag Todorovic · Berlin, DE
Miles Trumper · Loughborough, GB

Key dates

Filing date	Jul 3, 2012
Grant date	Oct 7, 2014
Priority date	—
Expiry date	Sep 15, 2032

Classification

Technology area (CPC F)Mechanical Engineering; Lighting; Heating
CPC primaryF02K1/827
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

Abstract

The present invention relates to an aircraft gas turbine with a core engine which is surrounded by a bypass duct enclosed radially outwards by a bypass wall, with a radially inner wall of the bypass duct forming with the radially outer bypass wall a bypass nozzle, and with the radially inner wall including an adjusting element extending along the circumference of the inner wall and being deformable radially outwards.

Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.