VENA CONTRACTA SWIRLING DILUTION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR

• US 20160201908A1
• Filed: 06/30/2014
• Published: 07/14/2016
• Est. Priority Date: 08/30/2013
• Status: Abandoned Application

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Drake, Christopher, Cunha, Frank J., Kostka, Stanislav Jr., Jause, Jonathan M., Hanson, Russell B.
• Application Number:
  US14/910,856
• Publication Number:
  US 20160201908A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03042 Film cooled combustion chamber walls or domes
• CPC Class Codes: F23R 2900/03044 Impingement cooled combustion chamber walls or subassemblies
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: F23R 3/04 Air inlet arrangements
• CPC Class Codes: F23R 3/045 using pipes
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: F23R 3/26 Controlling the air flow
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A liner panel for use in a combustor of a gas turbine engine includes a nozzle includes an inner periphery along an axis. The inner periphery includes a flow guide around the axis. A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis. The wall assembly also includes a liner panel with a second inner periphery along the axis, the second inner periphery including a spiral flow guide around the axis. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine includes contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.

Claims

1. A liner panel for use in a combustor of a gas turbine engine, the liner panel comprising a nozzle including an inner periphery along an axis, said inner periphery including a flow guide around said axis.

2. The liner panel as recited in claim 1, wherein said inner periphery has a circular cross section.

3. The liner panel as recited in claim 1, wherein said inner periphery has an oval cross section.

4. The liner panel as recited in claim 1, wherein said inner periphery is defined by a grommet.

5. The liner panel as recited in claim 1, wherein said flow guide extends from said inner periphery.

6. The liner panel as recited in claim 1, wherein said inner periphery includes a spiral flow guide.

7. The liner panel as recited in claim 1, wherein said flow guide extends from said inner periphery and at least partially around said axis.

8. A wall assembly for use in a combustor of a gas turbine engine, the wall assembly comprising:

a support shell with a first inner periphery along an axis; and

a liner panel with a second inner periphery along said axis, said second inner periphery including a spiral flow guide around said axis.

9. The wall assembly as recited in claim 8, wherein said first inner periphery and said second inner periphery each has an oval cross-section.

10. The wall assembly as recited in claim 8, wherein said first inner periphery and said second inner periphery define a dilution passage.

11. The wall assembly as recited in claim 8, further comprising:

an inner wall extending along the axis and operatively disposed between the first inner periphery and the second inner periphery;

wherein said first inner periphery and/or said second inner periphery has a circular cross-section.

12. The wall assembly as recited in claim 8, further comprising:

a contoured inner wall is defined between the first inner periphery and the second inner periphery;

wherein said first inner periphery and/or said second inner periphery has an oval cross section.

13. The wall assembly as recited in claim 8, wherein said spiral flow guide extends from said second inner periphery.

14. The wall assembly as recited in claim 8, wherein said spiral flow guide extends from said second inner periphery and at least partially around said axis.

15. A method of reducing recirculation into a dilution passage in a combustor liner panel of a gas turbine engine, the method comprising contouring a dilution passage to match a natural vena contracta of a fluid flowing therethrough.

16. The method as recited in claim 15, further comprising swirling the dilution air jet to hug an inner periphery of the dilution passage.

17. The method as recited in claim 15, wherein the contouring the dilution passage includes defining a flow guide within the inner periphery of the dilution passage.

18. The method as recited in claim 15, wherein the contouring the dilution passage includes defining a flow guide around an axis defined by the dilution passage.

19. The method as recited in claim 15, wherein the contouring the dilution passage includes defining a swirl flow guide inner periphery of the dilution passage.

20. The method as recited in claim 15, wherein the contouring the dilution passage includes defining a non-axial symmetric inner periphery.