System for supporting a turbine nozzle

Patent metadata

Field	Value
Publication number	US-9528392-B2
Application number	US-201313891441-A
Country	US
Kind code	B2
Filing date	May 10, 2013
Priority date	May 10, 2013
Publication date	Dec 27, 2016
Grant date	Dec 27, 2016

Abstract

A system for supporting a turbine nozzle includes an inner barrel having a forward end, an aft end and an outer surface that extends between the forward end and the aft end. A first fitting that extends through the outer surface is defined within the inner barrel. The system further includes a nozzle support ring that defines a second fitting that is complementary to the first fitting defined within the inner barrel.

First claim

What is claimed is:

1. A system for supporting a turbine nozzle, comprising:
an inner barrel having a forward end, an aft end, an inner surface and an outer surface that extends between the forward end and the aft end;
a slot defined within the inner barrel and extending circumferentially along and axially within the outer surface of the inner barrel, wherein the slot comprises a recess extending axially forward from the slot within the inner barrel; and
a nozzle support ring having a forward portion and an aft portion, wherein the aft position is axially offset from the slot and the inner barrel, wherein the forward portion defines a tab that is complementary to and extends axially into the recess of the slot, and wherein the aft portion is coupled to a first stage of turbine nozzles.

2. The system as in claim 1 , further comprising a locking pin that extends radially between the slot and the forward portion of the nozzle support ring.

3. The system as in claim 1 , wherein the nozzle support ring comprises two or more semi-annular support ring sections.

4. A combustion section of a gas turbine, comprising:
a compressor discharge casing;
a turbine nozzle disposed within the compressor discharge casing;
an inner barrel disposed within the compressor discharge casing, the inner barrel being axially separated from the turbine nozzle within the compressor discharge casing, the inner barrel having a forward end, an aft end and an outer surface that extends between the forward end and the all end;
a slot defined by the inner barrel proximate to the aft end and extending circumferentially along and axially within the outer surface of the inner barrel, wherein the slot comprises a recess extending axially forward from the slot within the inner barrel;
a nozzle support ring having a forward portion and an aft portion axially spaced from the forward portion, the forward portion defining a tab that is complementary to the slot; and
wherein the forward portion extends radially into the slot and the tab extends axially into the recess, wherein the aft portion is coupled to an inner band of the turbine nozzle.

5. The combustion section as in claim 4 , wherein the tab is seated within the slot.

6. The combustion section as in claim 4 , wherein the slot extends circumferentially around a diffuser casing.

7. The combustion section as in claim 4 , further comprising a locking pin that extends radially between the slot and the tab of the nozzle support ring.

8. The system as in claim 1 , wherein the nozzle support ring extends axially across a portion of the outer surface of the inner barrel.

9. A gas turbine, comprising:
a. a compressor;
b. a combustion section disposed downstream from the compressor;
c. a turbine disposed downstream from the combustion section;
d. a turbine nozzle disposed at an inlet to the turbine; and
e. wherein the combustion section includes a compressor discharge casing that circumferentially surrounds a system for supporting the turbine nozzle, the system comprising:
i. an inner barrel that extends within the compressor discharge casing, the inner barrel being axially separated from the turbine nozzle, the inner barrel having a forward end, an aft end and an outer surface that extends between the forward end and the aft end;
ii. a slot defined by the inner barrel proximate to the aft end and extending circumferentially along the outer surface of the inner barrel, wherein the slot comprises a recess extending axially forward from the slot within the inner barrel;
iii. a nozzle support ring having a forward portion and an aft portion axially offset from the forward portion, the forward portion defining a tab that is complementary to the slot; and
iv. wherein the forward portion extends radially into the slot and the tab extends axially into the recess, and wherein the aft portion is connected to an inner band of the turbine nozzle.

10. The gas turbine as in claim 9 , wherein the tab is seated within the slot.

11. The gas turbine as in claim 9 , further comprising a locking pin that extends radially between the slot and the tab.

12. The gas turbine as in claim 9 , wherein the nozzle support ring extends axially across a portion of the outer surface of the inner barrel.

Assignees

• Gen Electric

Inventors

• Casavant Matthew Stephen
• Black Kenneth Damon

Classifications

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title