Combustor dome heat shield

Patent metadata

Field	Value
Publication number	US-9982890-B2
Application number	US-201314085011-A
Country	US
Kind code	B2
Filing date	Nov 20, 2013
Priority date	Nov 20, 2013
Publication date	May 29, 2018
Grant date	May 29, 2018

Abstract

A combustor heat shield has lips with fins distributed on the lips. The lip-fins have an extended end portion projecting rearwardly from the back face of the heat shield. Impingement jets may be directed against the rearwardly extended end portions of the lip-fins to enhance cooling. The heat shield may define a fuel nozzle opening surrounded by a rail on the back side of the heat shield. Impingement holes or slots may be defined in the rail for allowing cooling air passing therethrough to impinge upon the lip-fins.

First claim

What is claim is:

1. A heat shield for a combustor of a gas turbine engine, the heat shield comprising:
a heat shield panel adapted to be mounted to an inside of a dome of the combustor with a back face of the heat shield panel in a spaced-apart facing relationship with an inner surface of the dome, the heat shield configured to receive a flow of cooling air along the back face of the heat shield panel;
at least one radially inner lip or radially outer lip along a periphery of the heat shield panel and projecting forwardly from a forward face of the heat shield panel, the at east one of the radially inner lip or radially outer lip having a radially facing surface; and
an array of lip-fins projecting radially from the radially facing surface of the at least one of the radially inner lip or radially outer lip, the lip-fins having extended end portions projecting rearwardly beyond the back face of the heat shield panel, the lip-fins also extending forwardly relative to the back face of the heat shield panel.

2. The heat shield defined in claim 1 , wherein a rail projects from the back face of the heat shield panel about at least one fuel nozzle opening defined in the heat shield panel, and wherein a set of impingement passages is defined in said rail, the impingement passages being oriented toward said extended end portions of the lip-fins.

3. The heat shield defined in claim 1 , wherein cooling passages are defined in said heat shield panel, said cooling passages being oriented toward said extended end portions of the lip-fins.

4. The heat shield defined in claim 3 , wherein the cooling passages are defined in a structure projecting rearwardly from the back face of the heat shield panel, the structure being integral with the back face of the heat shield panel.

5. The heat shield defined in claim 4 , wherein the structure includes a rail, and wherein the cooling passages are defined in the rail.

6. The heat shield defined in claim 5 , wherein the cooling passages have an angular orientation relative to the back face of the heat shield panel.

7. The heat shield defined in claim 6 , wherein the rail is an outer rail surrounding an inner ring on the back face of the heat shield panel about a fuel nozzle opening, and wherein a respective centerline of each impingement passage clears the inner ring.

8. A combustor comprising:
a combustor shell circumscribing a combustion chamber, the combustor shell having a dome;
at least one circumferential array of dome heat shield panels mounted to an inner side of the dome, the dome heat shield panels each having a forward face and a back face disposed in a spaced-apart facing relationship with the inner side of the dome, the back faces of the dome heat shield panels and the inner side of the dome defining can air gap therebetween;
each of the dome heat shield panels respectively having a radially inner lip and a radially outer lip, the radially inner lip and the radially outer lip each projecting forwardly from the forward face and between opposed lateral edges, the radially inner lip and radially outer lip each having a radially facing surface; and
inner and outer arrays of lip-fins respectively provided along the radially inner lip and radially outer lip of each dome heat shield panel, the lip-fins projecting radially from the respective radially facing surfaces of each radially inner lip and radially outer lip, the lip-fins having extended end portions projecting rearwardly beyond the back face of each of the dome heat shield panels, the lip-fins also extending forwardly relative to the back face of each of the dome heat shield panels.

9. The combustor defined in claim 8 , further comprising impingement passages defined in each of the dome heat shield panels, the impingement passages being oriented toward the extended end portions of the lip-fins.

10. The combustor defined in claim 9 , wherein the impingement passages are defined in respective sealing rails extending rearwardly from the back side of each of the dome heat shield panels.

11. The combustor defined in claim 10 , wherein at least one fuel nozzle opening is defined in each of the dome heat shield panels, and wherein the sealing rails of each of the dome heat shield panels include an annular rail extending about the at least one fuel nozzle opening of each of the dome heat shield panels, the impingement passages being defined in said annular rail of each of the dome heat shield panels.

12. The combustor defined in claim 11 , wherein the impingement passages are inclined relative to the back face of each of the dome heat shield panels, wherein the annular rail is an outer rail surrounding an inner ring on the back face of each dome heat shield panel, and wherein a respective centerline of each impingement passage clears the inner ring.

13. The combustor defined in claim 9 , wherein each of said impingement passages has an inlet end in fluid flow communication with said air gap.

14. The combustor defined in claim 8 , further comprising inner and outer front heat shield panels respectively mounted to radially inner and outer liners of the combustor shell, the inner and outer front heat shield panels having respective overlapping portions which overlap the inner and outer lips of the dome heat shield panels and define respective clearances therewith, the inner and outer lips of the dome heat shield panels being adjacent to the respective overlapping portions of the inner and outer front heat shield panels, respective front surfaces of said respective overlapping portions of the inner and outer front heat shield panels having no thermal barrier coating.

15. The combustor defined in claim 14 , wherein the the inner and outer front heat shield panels each have a respective thermal barrier coating applied thereto outwardly of the respective overlapping portions, wherein the thicknesses of the thermal barrier coatings taper from a full thickness to zero at said respective overlapping portions.

16. A method of cooling combustor heat shield panels mounted in a combustor of a gas turbine engine, the method comprising:
convection cooling a heat shield panel by passing coolant through impingement passages defined in the heat shield panel;
impingement cooling the heat shield panel by directing coolant discharged from the impingement passages against extended end portions of peripheral lip-fins projecting radially from respective peripheral lips extending along radially inner and outer sides of the heat shield panel, the peripheral lip-fins and the peripheral lips protecting forwardly from a forward face of the heat shield panel, the extended end portions of the peripheral lip-fins projecting rearwardly beyond a back face of the heat shield panel; and
convection cooling the peripheral lip-fins, using the coolant directed against the extended end portions of the peripheral lip-fins, by directing the coolant which has impinged against the extended end portions of the peripheral lip-fins forwardly over the peripheral lip-fins along the peripheral lips of the heat shield panel.

17. The method defined in claim 16 , wherein the heat shield panel is a dome heat shield panel and is mounted to a dome of the combustor, and wherein the method further comprises using the coolant flowing over the peripheral lip-fins along the peripheral lips to form a coolant film over respective front faces of adjacent radially inner and radially outer front heat shield panels respectively mounted, adjacent to the dome heat shield panel, to radially inner and radially outer liners of the combustor.

Assignees

• Pratt & Whitney Canada

Inventors

• Papple Michael
• Sze Robert
• Sreekanth Sri

Classifications

• F23R2900/00019

  Repairing or maintaining combustion chamber liners or subparts · CPC title

• F23R3/16 Primary

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title

• F23R3/045

  using pipes · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title