Nozzle support system

Patent metadata

Field	Value
Publication number	US-10451003-B2
Application number	US-201514923669-A
Country	US
Kind code	B2
Filing date	Oct 27, 2015
Priority date	Oct 28, 2014
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

A nozzle support system for a nozzle of a gas turbine includes an outer ring, an inner ring disposed within the outer ring, and a plurality of links pivotally attaching the outer ring to the inner ring. Each one of the links may have an outer end that is pivotally attached to the outer ring, and each one of the links may have an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring.

First claim

What is claimed is:

1. A nozzle support system for a gas turbine, comprising:
an outer ring;
an inner ring disposed within the outer ring;
a plurality of links pivotally attaching the outer ring to the inner ring; and
a plurality of vanes extending along a radial direction between the inner and outer rings, each one of the vanes having a radially inner end at a different axial location than a radially outer end of the respective vane, and each one of the vanes defining a passage that has a respective one of the links disposed therein;
wherein each one of the links has an outer end that is pivotally attached to the outer ring, and each one of the links has an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring; and
wherein the outer end of each link is pivotally attached to the outer ring at a different axial location than where the inner end of each link is pivotally attached to the inner ring such that the link forms an acute angle with the longitudinal axis.

2. The nozzle support system of claim 1 , wherein the coefficient of thermal expansion of the outer ring is greater than the coefficient of thermal expansion of the inner ring.

3. The nozzle support system of claim 2 , wherein the coefficient of thermal expansion of the outer ring is greater than the coefficient of thermal expansion of the plurality of links.

4. The nozzle support system of claim 3 , wherein the inner ring is configured to carry a center body in a forward direction with respect to the outer ring along the longitudinal axis of the outer ring, in response to a thermal expansion of the nozzle support system.

5. The nozzle support system of claim 1 , wherein the inner ring is a conical front end portion of a cylindrical body configured to carry a tail cone.

6. The nozzle support system of claim 1 , wherein the links are spaced apart from one another about the circumference of the inner ring.

7. The nozzle support system of claim 1 , further comprising a plurality of pin fasteners configured to pivotally attach a respective one of the outer ends of the links to the outer ring.

8. The nozzle support system of claim 1 , further comprising a plurality of pin fasteners configured to pivotally attach a respective one of the inner ends of the links to the inner ring.

9. A nozzle, comprising:
a nozzle support system having an outer ring, an inner ring disposed within the outer ring, and a plurality of links pivotally attaching the outer ring to the inner ring;
an outer support structure attached to the outer ring;
a center body attached to the inner ring and defining an inner diameter of a flow path configured to pass an exhaust gas; and
a plurality of vanes extending along a radial direction between the inner and outer rings, each one of the vanes having a radially inner end at a different axial location than a radially outer end of the respective vane, and each one of the vanes defining a passage that has a respective one of the links disposed therein;
wherein each one of the links has an outer end that is pivotally attached to the outer ring, and each one of the links has an inner end is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring; and
wherein the outer end of each link is pivotally attached to the outer ring at a different axial location than where the inner end of each link is pivotally attached to the inner ring such that the link forms an acute angle with the longitudinal axis.

10. The nozzle of claim 9 , further comprising a seal, and at least one of the outer ring, the inner ring and the links has a coefficient of thermal expansion configured to urge the center body against the seal in response to thermal expansion of the nozzle support system.

11. The nozzle of claim 9 , wherein the coefficient of thermal expansion of the outer ring is greater than the coefficient of thermal expansion of the inner ring.

12. The nozzle of claim 11 , wherein the coefficient of thermal expansion of the outer ring is greater than the coefficient of thermal expansion of the plurality of links.

13. The nozzle of claim 12 , wherein the center body is made of at least one of a metallic, a ceramic, a composite, and a ceramic matrix composite material.

14. The nozzle of claim 9 , wherein the inner ring is configured to carry the center body in a forward direction with respect to the outer ring along the longitudinal axis of the outer ring, in response to thermal expansion of the nozzle support system.

15. The nozzle of claim 9 , further comprising a plurality of pin fasteners configured to pivotally attach a respective one of the outer ends of the links to the outer ring.

16. The nozzle of claim 9 , further comprising a plurality of pin fasteners configured to pivotally attach a respective one of the inner ends of the links to the inner ring.

17. A gas turbine, comprising:
a combustor configured to generate an exhaust gas;
a nozzle disposed downstream of the combustor; and
a plurality of vanes extending along a radial direction between the inner and outer rings, each one of the vanes having a radially inner end at a different axial location than a radially outer end of the respective vane, and each one of the vanes defining a passage that has a respective one of the links disposed therein;
wherein the nozzle includes a nozzle support system having an outer ring, an inner ring and a plurality of links pivotally attaching the outer ring to the inner ring;
wherein the nozzle further includes an outer support structure attached to the outer ring;
wherein the nozzle further includes a center body attached to the inner ring and defining an inner diameter of an annular flow path configured to pass the exhaust gas therethrough;
wherein each one of the links has an outer end that is pivotally attached to the outer ring, and each one of the links has an inner end that is pivotally attached to the inner ring, such that the inner ring moves along a longitudinal axis of the outer ring; and
wherein the outer end of each link is pivotally attached to the outer ring at a different axial location than where the inner end of each link is pivotally attached to the inner ring such that the link forms an acute angle with the longitudinal axis.

18. The gas turbine of claim 17 , further comprising a seal, and at least one of the outer ring, the inner ring and the links has a coefficient of thermal expansion configured to urge the center body in a direction, which in turn urges the seal one of toward and away from a turbine, in response to the nozzle support system receiving heat.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Sutterfield David L
• Yount Randall E

Classifications

• F02C3/04

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

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D25/16

  Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) · CPC title

• F16M11/06

  allowing pivoting · CPC title