Fuel injector nozzle for combustion turbine engines including thermal stress-relief vanes

Patent metadata

Field	Value
Publication number	US-11274831-B2
Application number	US-201716482061-A
Country	US
Kind code	B2
Filing date	Mar 13, 2017
Priority date	Mar 13, 2017
Publication date	Mar 15, 2022
Grant date	Mar 15, 2022

Abstract

A fuel injection nozzle for a combustion turbine engine has thermal stress-relief vanes, which accommodate and relieve localized thermal stresses within its monolithic, three-dimensional nozzle structure, imparted by heat transfer during engine combustion. At least one first vane is coupled to opposing, spaced nozzle sleeves at both ends. At least one cantilever-like second vane is coupled to one of the opposing sleeves on one end, while the other free or floating end is spaced by a second vane gap from the other opposing sleeve. Some embodiments include a plurality of second vanes, which have locally varying orientation, and/or structure, and/or second vane gaps, for normalizing spatially and/or temporally thermal stresses within the nozzle structure. The monolithic structure is fabricated, in some nozzle embodiments, by additive manufacturing.

First claim

What is claimed is:

1. A fuel injector nozzle for a gas turbine engine, comprising:
first and second annular sleeves respectively having inner and outer circumferential walls, and axial length, the sleeves nested, concentrically aligned, and radially spaced;
a first fluid passage defined between the inner circumferential wall of the first sleeve and the outer circumferential wall of the second sleeve;
a first discharge opening at a downstream axial end of the first fuel injector nozzle, in fluid communication with the first fluid passage;
a first vane having a first end coupled to the inner circumferential wall of the first sleeve, and a second end coupled to the outer circumferential wall of the second sleeve;
a second vane, circumferentially or axially spaced from the first vane, having a first end coupled to only one of the inner circumferential wall of the first sleeve or the outer circumferential wall of the second sleeve, and a second end in a radially opposed and spaced relationship with the other, non-coupled circumferential wall of the first sleeve or the second sleeve, defining a second vane gap there between;
wherein the first and second annular sleeves, and the first and second vanes are formed in a monolithic, three-dimensional structure,
wherein the first vane comprises a plurality of rows of axially spaced first vanes, each respective first vane having a first end coupled to the inner circumferential wall of the first sleeve, and a second end coupled to the outer circumferential wall of the second sleeve; and
wherein the second vane comprises a plurality of rows of axially spaced second vanes, corresponding to and circumferentially spaced from each of the plurality of rows of axially spaced first vanes, each respective second vane having a first end coupled to only one of the inner circumferential wall of the first sleeve or the outer circumferential wall of the second sleeve, and a second end in a radially opposed and spaced relationship with the other, non-coupled circumferential wall of the first sleeve or the second sleeve, defining a second vane gap there between.

2. The fuel injector nozzle of claim 1 , wherein the plurality of rows of axially spaced first vanes is oriented at different circumferential positions about the second sleeve.

3. The fuel injector nozzle of claim 1 , wherein the plurality of rows of axially spaced second vanes respectively defining different second vane gaps.

4. The fuel injector nozzle of claim 3 , wherein the second vane gaps for each respective second vane being respectively arranged to compensate for variations in localized thermal expansion between the second vane and the first and second sleeves.

5. A combustor for a combustion section of a gas turbine engine, including the fuel injector nozzle of claim 1 , further comprising:
a fuel delivery system coupled proximal to an upstream end of the fuel injector nozzle, in fluid communication with the first fluid passage, for delivering fuel out of the first discharge opening at the downstream axial end of the fuel injector nozzle;
a first airflow through passage, having a first outlet that is in communication with the downstream axial end of the first fuel injector nozzle, for delivering compressed air to the downstream axial end of the first fuel injector nozzle; and
a combustion chamber oriented downstream of the downstream axial end of the fuel injector nozzle and the first outlet of the airflow through passage, for enveloping compressed air exhausted from the first outlet of the airflow through passage, fuel exhausted from the first discharge opening, fuel and air mixture and combustion gas in a combustion zone of the combustion chamber.

6. A fuel injector nozzle for a gas turbine engine, comprising:
first, second and third annular sleeves, respectively having inner and outer circumferential walls, and axial length, the sleeves nested, concentrically aligned, and radially spaced;
a first fluid passage defined between the inner circumferential wall of the first sleeve and the outer circumferential wall of the second sleeve;
a first discharge opening at a downstream axial end of the first fuel injector nozzle, in fluid communication with the first fluid passage;
a second fluid passage defined between the inner circumferential wall of the second sleeve and the outer circumferential wall of the third sleeve;
a second discharge opening at the downstream axial end of the first fuel injector nozzle, in fluid communication with the second fluid passage;
a first vane having a first end coupled to the inner circumferential wall of the first sleeve, and a second end coupled to the outer circumferential wall of the second sleeve;
a second vane, circumferentially or axially spaced from the first vane, having a first end coupled to only one of the inner circumferential wall of the first sleeve or the outer circumferential wall of the second sleeve, and a second end in a radially opposed and spaced relationship with the other, non-coupled circumferential wall of the first sleeve or the second sleeve, defining a second vane gap there between;
a third vane having a first end coupled to the inner circumferential wall of the second sleeve, and a second end coupled to the outer circumferential wall of the third sleeve; and
a fourth vane, circumferentially or axially spaced from the third vane, having a first end coupled to only one of the inner circumferential wall of the second sleeve or the outer circumferential wall of the third sleeve, and a second end in a radially opposed and spaced relationship with the other, non-coupled circumferential wall of the second sleeve or the third sleeve, defining a fourth vane gap there between;
the first, second and third annular sleeves, and the first, second, third and fourth vanes formed in a monolithic, three-dimensional structure.

7. The fuel injector nozzle of claim 6 , the first and third vanes oriented at different circumferential positions about the second sleeve and/or at different axial positions along the second sleeve.

8. The fuel injector nozzle of claim 6 , wherein a respective plurality of the second vanes and/or a respective plurality of the fourth vanes being oriented at different circumferential positions about the second sleeve and/or at different axial positions along the second sleeve.

9. The fuel injector nozzle of claim 8 , wherein the plurality of the second vanes respectively defining different second vane gaps.

10. The fuel injector nozzle of claim 9 , wherein dimensions of the respective second vane gaps are formed by selectively adjusting length between the first and second ends of the second vanes, during formation of the monolithic structure.

11. The fuel injector nozzle of claim 9 , wherein the second vane gaps for each respective second vane being respectively arranged to compensate for variations in localized thermal expansion between the second vane and the first and second sleeves.

12. The fuel injector nozzle of claim 11 , wherein dimensions of the respective second vane gaps formed by selectively adjusting length between the first and second ends of the second vanes, during formation of the monolithic structure.

13. The fuel injector nozzle of claim 8 , wherein a plurality of the fourth vanes respectively defining different fourth vane gaps.

14. The fuel injector nozzle of claim 13 , wherein dimensions of the respective fourth vane gaps are formed by selectively adjusting length between the first and second ends of the fourth vanes, during formation of the monolithic structure.

15. The fuel injector nozzle of claim 13 , wherein the fourth vane gap

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• Sanchez Fabian Enrique

Classifications

• F23R3/28 Primary

  characterised by the fuel supply (burners F23D) · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23D11/38

  Nozzles; Cleaning devices therefor · CPC title

• F23R2900/00004

  Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits · CPC title

• F23D11/107

  at least one of both being subjected to a swirling motion · CPC title