ENGINE COWLING OF AN AIRCRAFT GAS TURBINE

• US 20160288916A1
• Filed: 03/31/2016
• Published: 10/06/2016
• Est. Priority Date: 04/02/2015
• Status: Active Grant

• Current Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Inventors: TODOROVIC, Predrag
• Granted Patent: US 10,442,543 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 27/16 of jet type
• CPC Class Codes: B64D 27/18 within, or attached to, wings
• CPC Class Codes: B64D 29/00 Power-plant nacelles, fairings, or cowlings nacelles not otherwise provided for B64C
• CPC Class Codes: B64D 29/02 associated with wings wings adapted for mounting power plant B64C
• CPC Class Codes: B64D 29/04 associated with fuselages
• CPC Class Codes: B64D 29/06 Attaching of nacelles, fairings or cowlings
• CPC Class Codes: B64D 29/08 Inspection panels for power plants
• CPC Class Codes: F02K 1/09 by axially moving an external member, e.g. a shroud F02K1/12 takes precedence
• CPC Class Codes: F02K 1/72 the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• CPC Class Codes: F05D 2230/72 Maintenance
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

The invention relates to an engine cowling of an aircraft gas turbine which has a rear area that comprises at least two doors that are arranged at the bottom area of the rear area of the engine cowling and are to be opened by means of overhead hinges, wherein the hinges are arranged so as to be tilted with respect to the engine axis.

Claims

1. An engine cowling of an aircraft gas turbine that has a rear area which comprises at least two doors, which are arranged at the bottom area of the rear area of the engine cowling and are to be opened by means of overhead hinges, wherein the hinges are arranged so as to be tilted with respect to the engine axis.

2. The engine cowling according to claim 1, wherein the doors are mounted laterally and so that they can be swiveled backwards.

3. The engine cowling according to claim 1, wherein the hinges are arranged below a substantially horizontal central plane of the aircraft gas turbine which contains the engine axis.

4. The engine cowling according to claim 1, wherein the doors are supported in the various opening states by means of dampers.

5. The engine cowling according to claim 4, wherein the dampers are embodied as piston-cylinder units, in particular as gas pressure absorbers.

6. The engine cowling according to claim 4, wherein the dampers act in a toggle-lever-like manner and/or support an opening process or a closing process of the doors.

7. The engine cowling according to claim 1, wherein the rear area of the engine cowling is embodied so that it can be displaced in the axial direction.

8. The engine cowling according to claim 1, wherein thrust reversal elements are mounted in the rear area of the engine cowling.

9. The engine cowling according to claim 1, wherein a core engine cowling is provided with inspection doors in the area of the doors of the rear area of the engine cowling.

10. The engine cowling according to claim 9, wherein the inspection doors can be operated independently of the doors of the rear area of the engine cowling.