Combustor inlet mixing system with swirler vanes having slots

Patent metadata

Field	Value
Publication number	US-2018003384-A1
Application number	US-201515538879-A
Country	US
Kind code	A1
Filing date	Jan 22, 2015
Priority date	Jan 22, 2015
Publication date	Jan 4, 2018
Grant date	—

Abstract

A combustor inlet mixing system ( 10 ) formed from a plurality of circumferentially spaced swirler vanes ( 38 ) extending radially outward from a nozzle hub. Each of the swirler vanes ( 38 ) may have a length ( 62 ) that extends downstream along at least a portion of the combustor inlet mixing system ( 10 ), and may further have a thickness ( 66 ) that extends along a circumference of the nozzle hub. At least one of the swirler vanes ( 38 ) may further have at least one slot ( 42 ) cut entirely through the thickness ( 66 ) of a portion of the swirler vane ( 38 ). The slot ( 42 ) may separate the swirler vane ( 38 ) from the nozzle hub along a portion of the length ( 62 ) of the swirler vane ( 38 ).

First claim

It is claimed:

1 - 17 . (canceled)

18 . A turbine engine, comprising:
at least one combustor positioned upstream from a rotor assembly, wherein the rotor assembly includes at least one row of turbine blades extending radially outward from a rotor; a compressor positioned upstream from the at least one combustor; at least one compressor exhaust plenum extending between the compressor and the at least one combustor; and at least one combustor inlet mixing system formed from a plurality of circumferentially spaced swirler vanes extending radially outward from a nozzle hub, each of the plurality of swirler vanes having a length that extends downstream along at least a portion of the at least one combustor inlet mixing system and further having a thickness that extends along a circumference of the nozzle hub, wherein at least one swirler vane of the plurality of swirler vanes further has at least one slot cut entirely through the thickness of a portion of the at least one swirler vane, the at least one slot separating the at least one swirler vane from the nozzle hub along a portion of the length of the at least one swirler vane.

19 . The turbine engine of claim 18 , wherein the at least one slot is configured to add a layer of at least partially non-swirling air around the nozzle hub.

20 . The turbine engine of claim 18 , wherein the at least one slot is configured to add a layer of non-swirling air around the nozzle hub.

21 . The turbine engine of claim 18 , wherein the nozzle hub comprises a heat shield positioned downstream of the plurality of swirler vanes.

22 . The turbine engine of claim 18 , wherein the nozzle hub comprises a gas diffusion outlet positioned downstream of the plurality of swirler vanes.

23 . The turbine engine of claim 18 , wherein each of the plurality of swirler vanes has at least one slot cut entirely through the thickness of a portion of the each of the plurality of swirler vanes, the at least one slot of the each of the plurality of swirler vanes separating the each of the plurality of swirler vanes from the nozzle hub along a portion of the length of the each of the plurality of swirler vanes.

24 . The turbine engine of claim 18 , wherein each of at least half of the plurality of swirler vanes has at least one slot cut entirely through the thickness of a portion of the each of at least half of the plurality of swirler vanes, the at least one slot of the each of at least half of the plurality of swirler vanes separating the each of at least half of the plurality of swirler vanes from the nozzle hub along a portion of the length of the each of at least half of the plurality of swirler vanes.

25 . The turbine engine of claim 18 , wherein each of at least one fourth of the plurality of swirler vanes has at least one slot cut entirely through the thickness of a portion of the each of at least one fourth of the plurality of swirler vanes, the at least one slot of the each of at least one fourth of the plurality of swirler vanes separating the each of at least one fourth of the plurality of swirler vanes from the nozzle hub along a portion of the length of the each of at least one fourth of the plurality of swirler vanes.

26 . The turbine engine of claim 18 , wherein each of at least one third of the plurality of swirler vanes has at least one slot cut entirely through the thickness of a portion of the each of at least one third of the plurality of swirler vanes, the at least one slot of the each of at least one third of the plurality of swirler vanes separating the each of at least one third of the plurality of swirler vanes from the nozzle hub along a portion of the length of the each of at least one third of the plurality of swirler vanes.

27 . The turbine engine of claim 18 , wherein each of the plurality of swirler vanes has a curved contour.

28 . The turbine engine of claim 18 , wherein each of the plurality of swirler vanes has a twisted contour.

29 . The turbine engine of claim 18 , wherein the at least one slot separates the at least one swirler vane from the nozzle hub along at least one half of the length of the at least one swirler vane.

30 . The turbine engine of claim 18 , wherein the at least one slot separates the at least one swirler vane from the nozzle hub along at least one fourth of the length of the at least one swirler vane.

31 . The turbine engine of claim 18 , wherein the at least one swirler vane is manufactured with the at least one slot.

32 . The turbine engine of claim 18 , wherein the at least one swirler vane is modified to include the at least one slot.

33 . The turbine engine of claim 18 , wherein the nozzle hub comprises a pilot nozzle hub.

34 . The turbine engine of claim 18 , wherein the nozzle hub comprises a main nozzle hub and the plurality of swirler vanes comprise a plurality of main swirler vanes.

Assignees

• Siemens Ag

Inventors

• Wasif Samer P

Classifications

• F23C7/004

  using vanes · CPC title

• F01D9/041

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

• F01D5/143

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title