Vena contracta swirling dilution passages for gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-2016201908-A1
Application number	US-201414910856-A
Country	US
Kind code	A1
Filing date	Jun 30, 2014
Priority date	Aug 30, 2013
Publication date	Jul 14, 2016
Grant date	—

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.

First claim

What is claimed is:

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.

Assignees

• United Technologies Corp

Inventors

• Drake Christopher
• Cunha Frank J
• Kostka Jr Stanislav
• Jause Jonathan M
• Hanson Russell B

Classifications

• F23R3/26

  Controlling the air flow · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title