Infrared suppression system in a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10718229-B2
Application number	US-201615216365-A
Country	US
Kind code	B2
Filing date	Jul 21, 2016
Priority date	Jul 21, 2016
Publication date	Jul 21, 2020
Grant date	Jul 21, 2020

Abstract

According to one aspect, a system for alignment of vanes to suppress infrared detection in a gas turbine engine is provided. The system includes a first vane disposed on a first component, and a second vane disposed on a second component. The second vane is configured to engage the first vane such that the second component is capable of being positioned proximal to the first component.

First claim

We claim:

1. A system for alignment of vanes to suppress infrared detection in a gas turbine engine, comprising:
a substantially stationary first vane disposed on a first component, the substantially stationary first vane comprising a first transition portion;
a second vane disposed on a second component and movable relative to the substantially stationary first vane, the second vane comprising a second transition portion; and
an actuator disposed between the first component and the second component, wherein the second component is disposed downstream of the first component, and the actuator is configured to move the second component in a helical motion toward the first component to engage the second transition portion into mating arrangement with the first transition portion.

2. The system of claim 1 , wherein the first substantially stationary vane and the second vane are S-vanes.

3. The system of claim 1 , further comprising:
a guide track connected to the first component; and
a guide roller disposed in the guide track, wherein the guide roller is connected to the second component, the actuator is disposed between the first component and the second component.

4. The system of claim 3 , wherein the second component is guided via the guide roller travelling within the guide track in a reciprocating movement caused by the actuator toward and away from the first component.

5. The system of claim 1 , wherein the first component is a stationary blocker vane segment and the second component is a telescoping blocker vane segment.

6. A system for alignment of vanes to suppress infrared detection in a gas turbine engine, comprising:
a substantially stationary first vane disposed on a first component, the substantially stationary first vane comprising a first transition portion;
a second vane disposed on a second component and movable relative to the substantially stationary first vane, the second vane comprising a second transition portion; and
an actuator disposed between the first component and the second component, the actuator configured to move the second component toward the first component to engage the second transition portion into mating arrangement with the first transition portion, wherein the second transition portion rotates relative to a common central axis of the first and second components and into the first transition portion.

7. The system of claim 6 , wherein the first transition portion has a first radial pitch corresponding to a radial angle of rotation of the second transition portion such that the second transition portion rotates radially into the first transition portion.

8. The system of claim 7 , wherein the first transition portion has a first width and the second transition portion has a second width smaller than the first width such that the first and second transition portions can mate.

9. The system of claim 8 , wherein the substantially stationary first vane includes a first curved portion that extends away from the first transition portion in a first transverse direction and the second vane includes a second curved portion that extends away from the second transition portion in a second transverse direction opposite the first transverse direction.

10. The system of claim 9 , wherein the substantially stationary first vane and the second vane are in an engaged configuration to create a substantially open direct line-of-sight therebetween viewed along the common central axis of the first and second components.

11. The system of claim 9 , wherein the first vane and the second vane in a disengaged separated configuration create a substantially blocked direct line-of-sight viewed along the common central axis of the first and second components.

12. An infrared suppression system for a gas turbine engine, comprising:
a first exhaust component having a first plurality of substantially stationary vanes each of the first plurality of substantially stationary vanes comprising a first transition portion;
a second exhaust component having a second plurality of movable vanes, wherein each of the second plurality of movable vanes comprises a second transition portion, and wherein the first exhaust component and the second exhaust component are disposed on a common central axis; and
an actuator disposed between the first exhaust component and the second exhaust component, the actuator configured to cause the second exhaust component to reciprocate toward and away from the first exhaust component such that the second transition portions of each of the second plurality of movable vanes engage into corresponding first transition portions of the first plurality of substantially stationary vanes in a mating arrangement.

13. The infrared suppression system of claim 12 , wherein the first plurality of substantially stationary vanes and the second plurality of movable vanes are S-vanes.

14. The infrared suppression system of claim 12 , further comprising:
a guide track connected to the first exhaust component; and
a guide roller disposed in the guide track, wherein the guide roller is connected to the second exhaust component.

15. The infrared suppression system of claim 14 , wherein the first plurality of substantially stationary vanes and the second plurality of movable vanes are S-vanes, where the second plurality of movable vanes are configured to move in a reciprocating helical motion in relation to the first plurality of substantially stationary vanes such that the second transition portion mates with the first transition portion.

16. The infrared suppression system of claim 15 , wherein the first plurality of substantially stationary vanes and the second plurality of movable vanes are in an engaged configuration to create a substantially open direct line-of-sight therebetween viewed along the common central axis of the first and second exhaust components.

17. The infrared suppression system of claim 15 , wherein the first plurality of substantially stationary vanes and the second plurality of movable vanes are in a disengaged separated configuration to create a substantially blocked direct line-of-sight viewed along the common central axis of the first and second exhaust components such that an infrared signature of the gas turbine engine is suppressed.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Froemming Kenneth William
• Pesyna Kenneth M

Classifications

• F02K1/825

  Infrared radiation suppressors · CPC title

• F01D17/167

  of vanes moving in translation · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F02K1/36

  having an ejector · CPC title

• F02K1/82

  Jet pipe walls, e.g. liners · CPC title