Hot streak alignment for gas turbine durability

Patent metadata

Field	Value
Publication number	US-9581085-B2
Application number	US-201313836426-A
Country	US
Kind code	B2
Filing date	Mar 15, 2013
Priority date	Mar 15, 2013
Publication date	Feb 28, 2017
Grant date	Feb 28, 2017

Abstract

Embodiments of hot streak alignment for gas turbine durability include structures and methods to align hot streaks with the leading edges of aligned first stage nozzle vanes in order to improve mixing of the hot streaks with cooling air at a stator nozzle of a first stage turbine and reduce usage of cooling air at first stage non-aligned stator nozzle vanes disposed adjacent to the aligned stator vanes.

First claim

We claim:

1. A method of hot streak alignment to improve gas turbine durability, comprising:
igniting fuel and air at a combustor having a fuel nozzle thereby creating a hot streak of combustion gas;
aiming said hot streak at a leading edge of a stator nozzle vane;
providing one or more cooling holes disposed upon said stator nozzle vane adjacent to said leading edge;
passing cooling air through said vane and said one or more cooling holes adjacent said leading edge; and,
mixing of said combustion gas and cooling air to limit temperature of said combustion gas at downstream components;
further comprising:
a ratio of vanes to fuel nozzles being at least 2:1 wherein for a 2:1 ratio, the vanes are disposed within the stator nozzle in pairs, the pairs being made up of an aligned vane and a non-aligned vane;
the hot streak being directly aimed at the aligned vane, and not directly aimed at the non-aligned vane; and,
the step of passing said cooling air through said vane further comprises passing said cooling air through said aligned vane and through said non-aligned vane.

2. The method of claim 1 further comprising providing increased cooling flow on aligned stator nozzle vanes than on non-aligned vanes.

3. The method of claim 1 further comprising providing more of said cooling holes on aligned nozzle vanes than on non-aligned vanes.

4. The method of claim 1 further comprising directing a central point of said hot streak at said leading edge.

5. The method of claim 4 , said central point of said hot streak being at a center of said leading edge.

6. The method of claim 4 , said central point of said hot streak being spaced from a center of said leading edge.

7. The method of claim 1 , wherein the step of passing said cooling air further comprises providing a thin film of moving air moving through as well as over both of the aligned stator nozzle vane and the non-aligned stator nozzle vane.

8. The method of claim 1 , further comprising use of preferential cooling of the stator nozzles.

9. The method of claim 8 further comprising increasing cooling at other engine components by said preferential cooling.

10. The method of claim 9 further comprising decreasing cooling air usage at non-aligned vanes by said preferential cooling.

11. The method of claim 1 further comprising aligning said fuel nozzle radially with said aligned vane.

12. The method of claim 10 further comprising aligning said fuel nozzle circumferentially with said aligned vane.

13. The method of claim 1 , decreasing said cooling air at said non-aligned vanes relative to the cooling air provided to said aligned vanes.

14. A turbine engine, comprising:
a combustor having N number of fuel nozzles annularly arranged and spaced from one another;
a stator nozzle downstream from the combustor;
the stator nozzle further comprising N number of stator vanes axially aligned with and downstream from said N number of fuel nozzles; and,
the turbine engine further comprising a plurality of first stage rotating blades downstream of said aligned stator vanes of the stator nozzle;
further comprising M number of non-aligned stator vanes being disposed adjacent to and between each of the N number of aligned stator vanes.

15. The turbine engine of claim 14 wherein hot gas flows from a fuel nozzle within the combustor and through the combustor exit thereby impacting upon the stator nozzle and leading edges of said N number of aligned stator vanes receive said hot streaks.

16. The turbine engine of claim 14 wherein the hot streaks impinge on the N number of aligned vanes and the hot streaks mix with cooling air passing through the aligned vanes thereby aligning specific stator nozzle vanes.

17. The turbine engine of claim 16 wherein the aligning of specific nozzle vanes results in a decreased volume of cooling air required at the non-aligned nozzle vanes.

18. A method of improving vane durability in a gas turbine engine having N number of fuel nozzles disposed within N number of combustors and N number of aligned first turbine vanes comprises the steps of:
aligning the first stage vane airfoils circumferentially and axially opposite the N number of fuel nozzles;
blunting a hot streak of hot gas exiting the combustors with cooling air at a leading edge of the N number of the first stage aligned vanes, thereby reducing cooling air to M number of first stage non-aligned vanes; and,
increasing cooling air to alternate components of the gas turbine engine.

Assignees

• Gen Electric

Inventors

• Bartz Robert Joseph
• Bubnick Joseph Steven
• Bush Scott Matthew
• Feldmann Kevin Robert
• Frederick Robert Alan
• Higgins Craig William

Classifications

• F01D25/12

  Cooling · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F02C7/125 Primary

  by partial arc admission of the working fluid or by intermittent admission of working and cooling fluid · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title