Thrust deflecting device and aircraft engine

Patent metadata

Field	Value
Publication number	US-9664141-B2
Application number	US-201414299727-A
Country	US
Kind code	B2
Filing date	Jun 9, 2014
Priority date	Jun 12, 2013
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

A thrust deflecting device for deflecting a thrust stream is disclosed, which includes a flap system having a plurality of deflecting flaps, each of which is pivotable around its yaw axis, the flap system being situated between parallel control surfaces such as baffle plates which, together with the flap system, form a box structure, which is pivotable around a pivot axis running in the direction of the transverse axis for the purpose of deflecting the thrust stream in the pitch direction, an aircraft engine also being disclosed.

First claim

What is claimed is:

1. A thrust deflecting device for deflecting a thrust stream of an aircraft engine, the thrust deflecting device comprising:
a housing of the aircraft engine;
a flap system having a plurality of deflecting flaps, each deflecting flap pivotable around a yaw axis extending orthogonally with respect to a transverse axis of the thrust deflecting device; and
two parallel baffle plates extending downstream from the housing, the flap system situated between the two parallel baffle plates, the two parallel baffle plates together with the flap system being pivotable around a pivot axis running in the direction of the transverse axis for the purpose of deflecting the thrust stream in a pitch direction.

2. The thrust deflecting device as recited in wherein the housing has a transition from a circular cross section to an angular outlet cross section.

3. The thrust deflecting device as recited in claim 1 wherein the deflecting flaps are situated evenly distributed on both sides of a longitudinal axis of the thrust deflecting device, and the deflecting flaps on one side are pivotable in the opposite direction from the deflecting flaps on the other side.

4. The thrust deflecting device as recited in claim 3 wherein adjustment of the deflecting flaps in the opposite direction takes place via a translational movement of an actuator.

5. The thrust deflecting device as recited in claim 4 wherein an adjustment of the deflecting flaps in the same direction takes place via a translational transverse movement of an actuating housing accommodating the actuator.

6. The thrust deflecting device as recited in claim 4 wherein the actuator is linked to a sliding plate movable in the actuating housing in the longitudinal direction and operatively connected to each of the deflecting flaps on one side via a lever mechanism, the lever mechanisms each including a pivot body pivotable around a vertical axis extending parallel to the yaw axis of the deflecting flaps, joint rods extending from the pivot body to each of the deflecting flaps.

7. The thrust deflecting device as recited in claim 6 wherein the joint rods are linked to arms extending downstream from a front area of the deflecting flaps.

8. An aircraft engine comprising the thrust deflecting device as recited in claim 1 .

9. The thrust deflecting device as recited in claim 1 wherein the two parallel baffles plates are perpendicular to the plurality of deflecting flaps.

Assignees

• MTU Aero Engines AG

Inventors

• Klingels Hermann
• Klaen Stephan
• Scherer Christian
• Vogel Uwe

Classifications

• F02K1/80

  Couplings or connections · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• F02K1/006

  within one plane only · CPC title

• F02K1/008 Primary

  in any rearward direction · CPC title

• F05D2260/56

  using cams or eccentrics · CPC title