Expandable exhaust cone

Patent metadata

Field	Value
Publication number	US-10563620-B2
Application number	US-201615236047-A
Country	US
Kind code	B2
Filing date	Aug 12, 2016
Priority date	Aug 12, 2016
Publication date	Feb 18, 2020
Grant date	Feb 18, 2020

Abstract

An expandable exhaust cone assembly is described which is able to move from a collapsed position to an expanded position.

First claim

What is claimed is:

1. An expandable exhaust cone assembly adapted for use in an associated gas turbine engine, the expandable exhaust cone assembly comprising a fixed cone segment arranged around a central axis and adapted to be mounted to a structural component of the associated gas turbine engine, a plurality of movable cone segments configured to move from a collapsed position, associated with a first overall length of the expandable exhaust cone assembly along the central axis, to an expanded position, associated with a second overall length of the expandable exhaust cone assembly along the central axis that is longer than the first overall length, each of the plurality of movable cone segments nested within the fixed cone segment when the expandable exhaust cone assembly is in the collapsed position and arranged to extend outward of the fixed cone segment along the central axis when the expandable exhaust cone assembly is in the expanded position, and a cone mover configured to drive the plurality of movable cone segments from the collapsed position to the expanded position, and not from the expanded position to the collapsed position, in response to startup of the associated gas turbine engine, the cone mover comprising: a mover rod coupled to a turbine rotor of the associated gas turbine engine for rotation therewith, and a threaded plate coupled to the fixed cone segment, the mover rod having a threaded portion, the threaded portion engaged with the threaded plate when the cone segments are in the collapsed position and the threaded portion disengaged from the threaded plate when the cone segments are in the expanded position; or a gas pressure source in fluid communication with one of (a) a cavity comprising the plurality of movable cone segments and (b) an expandable substantially airtight tube connected to the plurality of movable cone segments, wherein the gas pressure source is operable to increase the pressure within the one of the cavity and the expandable substantially airtight tube above an external pressure outside the one of the cavity and the expandable substantially airtight tube.

2. The expandable exhaust cone assembly of claim 1 , wherein the cone mover comprises the mover rod coupled to the turbine rotor of the associated gas turbine engine for rotation therewith, and the threaded plate coupled to the fixed cone segment, the mover rod having the threaded portion, the threaded portion enqaqed with the threaded plate when the cone segments are in the collapsed position and the threaded portion disengaged from the threaded plate when the cone segments are in the expanded position, wherein the mover rod is configured to drive the plurality of movable cone segments to the expanded position in response to rotation of the turbine rotor.

3. The expandable exhaust cone assembly of claim 2 , wherein the cone mover includes an end cap, the end cap defining an end of the expandable exhaust cone assembly and the end cap not engaging the threaded portion of the mover rod so that the end cap is configured to allow rotation of the mover rod relative to the end cap.

4. The expandable exhaust cone assembly of claim 1 , wherein the cone mover comprises the gas pressure source in fluid communication with the expandable substantially airtight tube, the expandable substantially airtight tube having an internal volume smaller than an internal volume of the expandable exhaust cone assembly, the expandable substantially airtight tube coupled to the plurality of movable cone segments and adapted to be coupled to the gas pressure source so that the expandable substantially airtight tube is configured to drive the plurality of movable cone segments to the expanded position in response to a gas pressure increase within the expandable substantially airtight tube.

5. The expandable exhaust cone assembly of claim 4 , wherein the cone mover includes a lip coupled to the expandable substantially airtight tube and a non-expandable tube, the non-expandable tube is fixed relative to the fixed cone segment and has an internal volume smaller than the internal volume of the expandable substantially airtight tube and a sealable opening, the non-expandable tube is adapted to be coupled to the gas pressure source so that the non-expandable tube is configured to further drive the plurality of movable cone segments to the expanded position by being sealed by the lip and being released of the seal upon reaching a predetermined pressure value within the non-expandable tube in response to a gas pressure increase within the non-expandable tube from the gas pressure source.

6. The expandable exhaust cone assembly of claim 4 , wherein the cone mover includes a pressure relief mechanism configured to vent gas when gas pressure in the expandable substantially airtight tube exceeds a predetermined value.

7. The expandable exhaust cone assembly of claim 6 , wherein the pressure relief mechanism is selected from one of a pressure relief valve and a rupture disk.

8. The expandable exhaust cone assembly of claim 1 , wherein the cone mover comprises the gas pressure source in fluid communication with the cavity, the cavity having a variable volume the boundaries of which are created in part by the plurality of movable cone segments so that the gas pressure source is configured to drive the plurality of movable cone segments to the expanded position in response to a pressure increase within the cavity.

9. The expandable exhaust cone assembly of claim 8 , wherein the gas pressure source is selected from one of a gas from bypass air, a gas from exhaust air, and a gas from a pyrotechnic charge coupled to the associated gas turbine engine so that the pyrotechnic charge is configured to initiate startup of the associated gas turbine engine.

10. A cruise missile, the cruise missile comprising: a fuel supply tank, a gas turbine engine, the gas turbine engine comprising a compressor assembly, a combustor assembly, and a turbine assembly including a case and a rotor mounted in the case to rotate relative to the case, and an expandable exhaust cone assembly for use in the gas turbine engine, the expandable exhaust cone assembly comprising a fixed cone segment arranged around a central axis and mounted to a structural component of the gas turbine engine, a plurality of movable cone segments configured to move from a collapsed position, associated with a first overall length of the expandable exhaust cone assembly along the central axis, to an expanded position, associated with a second overall length of the expandable exhaust cone assembly along the central axis that is longer than the first overall length, and a cone mover configured to drive the plurality of movable cone segments from the collapsed position to the expanded position, and not from the expanded position to the collapsed position, in response to startup of the gas turbine engine, the cone mover comprising: a mover rod coupled to the rotor of the turbine assembly of the gas turbine engine for rotation therewith, and a threaded plate fixed relative to the fixed cone segment, the mover rod having a threaded portion, the threaded portion engaged with the threaded plate when the cone segments are in the collapsed position and the threaded portion disengaged from the threaded plate when the cone segments are in the expanded position; or a gas pressure source in fluid communication with one of (a) a cavity comprising the plurality of movable cone segments and (b) an expandable substantially airtight tube connected to the plurality of movable cone segments, wherein the gas pressure source is operable to increase the pressure within the one of the cavity and the expandable substantially airtight tube above an external pressure outside the

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Dierksmeier Douglas D
• Rice Edward C
• Humes Ryan C

Classifications

• F42B15/10

  Missiles having a trajectory only in the air · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F02K9/976 Primary

  Deployable nozzles · CPC title

• F02K1/08

  by axially moving or transversely deforming an internal member, e.g. the exhaust cone · CPC title