Thrust reverser with forward positioned blocker doors
US-2016369743-A1 · Dec 22, 2016 · US
Engine cowling of an aircraft gas turbine
US10202940B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10202940-B2 |
| Application number | US-201615093387-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 7, 2016 |
| Priority date | Apr 17, 2015 |
| Publication date | Feb 12, 2019 |
| Grant date | Feb 12, 2019 |
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- Title
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Abstract
Official abstract text for this publication.
An engine cowling of an aircraft gas turbine with a front area and a rear area that is displaceable in the axial direction, characterized in that the rear area is mounted and supported by means of multiple length-adjustable thrust reversal actuators that are arranged at an angle to one another.
First claim
Opening claim text (preview).
The invention claimed is: 1. An engine cowling of an aircraft gas turbine, comprising: a front area, and a rear area that is displaceable in an axial direction, a plurality of thrust reversal actuators that are length-adjustable and arranged at a non-zero angle to one another, the plurality of thrust reversal actuators each having a first end and a second end, the first ends being mounted to the aircraft gas turbine to support the plurality of thrust reversal actuators, wherein the rear area is directly mounted to, and supported by, the second ends of the plurality of thrust reversal actuators, wherein the plurality of thrust reversal actuators form a framework structure between the first ends and the rear area. 2. The engine cowling according to claim 1 , wherein the plurality of thrust reversal actuators are hinge mounted at at least one chosen from the first ends and the second ends. 3. The engine cowling according to claim 1 , wherein the plurality of thrust reversal actuators are hydraulic or electric actuators. 4. The engine cowling according to claim 1 , further comprising synchronization elements coupling the plurality of thrust reversal actuators to one another. 5. The engine cowling according to claim 1 , wherein the plurality of thrust reversal actuators are distributed around a circumference of the aircraft gas turbine. 6. The engine cowling according to claim 1 , wherein the rear area is axially displaceable into a cruise flight position, into a position for maximal thrust and into a thrust reversal position. 7. An engine cowling of an aircraft gas turbine, comprising: a front area, and a rear area that is displaceable in an axial direction, a plurality of thrust reversal actuators that are length-adjustable and arranged at a non-zero angle to one another, the plurality of thrust reversal actuators each having a first end and a second end, the first ends being mounted to the aircraft gas turbine to support the plurality of thrust reversal actuators, wherein the rear area is mounted to, and supported by, the second ends of the plurality of thrust reversal actuators, wherein the plurality of thrust reversal actuators form a framework structure between the first ends and the rear area, and rails extending in the axial direction, and arranged only in an upper area of the engine cowling. 8. An engine cowling of an aircraft gas turbine, comprising: a front area, and a rear area that is displaceable in an axial direction, a plurality of thrust reversal actuators that are length-adjustable and arranged at a non-zero angle to one another, the plurality of thrust reversal actuators each having a first end and a second end, the first ends being mounted to the aircraft gas turbine to support the plurality of thrust reversal actuators, wherein the rear area is mounted to, and supported by, the second ends of the plurality of thrust reversal actuators, wherein the plurality of thrust reversal actuators form a framework structure between the first ends and the rear area, wherein mounting positions of the second ends on the rear area are fixed in relationship to one another.
Assignees
Inventors
Classifications
Reversing fan flow · CPC title
- F02K1/625Primary
the aft end of the engine cowling being movable to uncover openings for the reversed flow · CPC title
Cross-Sectional Technologies · mapped topic
the axes being inclined in relation to each other · CPC title
- F02K1/72Primary
the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title
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- What does patent US10202940B2 cover?
- An engine cowling of an aircraft gas turbine with a front area and a rear area that is displaceable in the axial direction, characterized in that the rear area is mounted and supported by means of multiple length-adjustable thrust reversal actuators that are arranged at an angle to one another.
- Who is the assignee on this patent?
- Rolls Royce Deutschland Ltd & Co Kg
- What technology area does this patent fall under?
- Primary CPC classification F02K1/625. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Feb 12 2019 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).