Gas-turbine engine with telescope-type air inlet of the engine cowling (nacelle)

Patent metadata

Field	Value
Publication number	US-9719421-B2
Application number	US-201214122943-A
Country	US
Kind code	B2
Filing date	May 31, 2012
Priority date	Jun 1, 2011
Publication date	Aug 1, 2017
Grant date	Aug 1, 2017

Abstract

An aircraft gas-turbine engine has an engine cowling-nacelle which surrounds a core engine in a tubular way, characterized in that at least one inflow-side part of the engine cowling-nacelle is telescopically movable against the flow direction.

First claim

What is claimed is:

1. An aircraft gas-turbine engine comprising:
a core engine including a core engine casing,
an engine cowling spaced radially outwardly of the core engine casing and surrounding the core engine casing in a tubular manner forming a bypass duct, the engine cowling including an outer portion, an inner portion and an inflow-side part,
a fan connected to the core engine,
a bypass fan casing surrounding the fan and forming a portion of the bypass duct,
wherein the inflow-side part is tubular, extends around an entire circumference of the engine cowling, and is telescopically movable in a direction against the flow direction between a closed position and an open position,
wherein the inflow-side part includes a portion of the outer portion up to a thrust-reversing element of the gas-turbine engine and a portion of the inner portion positioned adjacent to the bypass fan casing when in the closed position,
wherein the portion of the inner portion is spaced apart from the bypass fan casing in the direction against the flow direction when in the open position.

2. The aircraft gas-turbine engine in accordance with claim 1 , wherein the portion of the inner portion extends downstream of a forward portion of the bypass fan casing in the flow direction.

3. The aircraft gas-turbine engine in accordance with claim 2 , and further comprising a seal positioned between the portion of the inner portion and the bypass fan casing for sealing between the portion of the inner portion and the bypass fan casing when the inflow-side part is in the closed position.

4. The aircraft gas-turbine engine in accordance with claim 3 , and further comprising telescopic rail guides mounting the inflow-side part.

5. The aircraft gas-turbine engine in accordance with claim 4 , wherein the telescopic rail guides provide to the inflow-side part at least one chosen from a substantially axial movement and at least a partly radial movement.

6. The aircraft gas-turbine engine in accordance with claim 2 , and further comprising telescopic rail guides mounting the inflow-side part.

7. The aircraft gas-turbine engine in accordance with claim 6 , wherein the telescopic rail guides provide to the inflow-side part at least one chosen from a substantially axial movement and at least a partly radial movement.

8. The aircraft gas-turbine engine in accordance with claim 1 , and further comprising telescopic rail guides mounting the inflow-side part.

9. The aircraft gas-turbine engine in accordance with claim 8 , wherein the telescopic rail guides provide to the inflow-side part at least one chosen from a substantially axial movement and at least a partly radial movement.

10. The aircraft gas-turbine engine in accordance with claim 1 , wherein the inflow-side part is movable by hand or by an auxiliary drive unit.

Assignees

• Todorovic Predrag
• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Todorovic Predrag

Classifications

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• F02C7/042 Primary

  having variable geometry · CPC title

• B64D2033/0286

  for turbofan engines · CPC title