Patent · US Active

Aircraft gas turbine comprising a thrust-reverser device with cascade elements and an integrated rack and pinion drive

US10012176B2 · kind B2 · utility

2Cited by

11References

5Claims

0Family size

Assignees

ROLLS-ROYCE DEUTSCHLAND LTD & CO KG · DE
LIEBHERR-AEROSPACE LINDENBERG GMBH · DE

Inventors

Predrag Todorovic · Berlin, DE
Josef Baer · Waltenhofen, DE
Frank Mueller · Wiehl, DE
Uwe Schümann · Pinneberg, DE

Key dates

Filing date	Dec 18, 2014
Grant date	Jul 3, 2018
Priority date	—
Expiry date	Dec 19, 2035

Classification

Technology area (CPC Y)Emerging Cross-Sectional Technologies
CPC primaryY02T50/60
WIPO fieldEngines, pumps, turbines
WIPO sectorMechanical engineering

Abstract

The present invention relates to an aircraft gas turbine comprising a thrust-reverser device that is arranged at the rear area of an engine cowling and that has multiple cascade elements which are distributed at the circumference and which divert a stream, characterized in that the cascade elements are mounted in a displaceable manner, in that on both sides of each cascade element at least one gear rack is formed that can be displaced via a respective cog wheel which is coupled to a driving device, and in that each cascade element is connected to a rear area of the engine cowling via a coupling element for the purpose of displacing the engine cowling in the axial direction.

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