Additive manufactured combustor heat shield

Patent metadata

Field	Value
Publication number	US-10935240-B2
Application number	US-201514694086-A
Country	US
Kind code	B2
Filing date	Apr 23, 2015
Priority date	Apr 23, 2015
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

A heat shield for use in a combustor of a gas turbine engine including a plurality of standoff pins that extend from a cold side, the plurality of standoff pins at least partially surround an attachment stud, the cold side including at least one film cooling hole adjacent to the plurality of standoff pins and the attachment stud.

First claim

What is claimed is:

1. A method of manufacturing a heat shield of a combustor for a gas turbine engine, the heat shield comprising a hollow attachment stud connected to a cold side of the heat shield by a stud end of the hollow attachment stud and configured to receive a nut at a free end of the hollow attachment stud, the heat shield further comprising a plurality of standoff pins that extend from the cold side, said plurality of standoff pins surrounding the hollow attachment stud, said plurality of standoff pins forming a ring pattern around said hollow attachment stud, said ring pattern of said plurality of standoff pins defining a diameter less than a diameter of said nut, wherein the hollow attachment stud comprises a cooling air passage along a central axis of said hollow attachment stud, at least one film cooling hole penetrating through the stud end of the hollow attachment stud and configured to discharge air from the cooling air passage to a hot side of the heat shield, and the hollow attachment stud further comprising a plurality of stud cooling holes that extends through said hollow attachment stud transverse to the central axis of said hollow attachment stud, said plurality of stud cooling holes arranged along a length of said hollow attachment stud between said cold side of said heat shield and said free end of the hollow attachment stud, the method comprising:
additively manufacturing the heat shield to form the heat shield with each of the hollow attachment stud and the plurality of standoff pins extending from the cold side and with a plurality of additional film cooling holes through said heat shield, at least one of said plurality of additional film cooling holes being adjacent to said plurality of standoff pins and said hollow attachment stud.

2. The method as recited in claim 1 , wherein additively manufacturing the heat shield further comprises additively manufacturing said plurality of standoff pins to be arranged in the ring pattern, said at least one of said plurality of additional film cooling holes being located within the diameter defined by said ring pattern.

3. A heat shield for use in a combustor of a gas turbine engine, the heat shield comprising:
a hollow attachment stud connected to a cold side of the heat shield by a stud end of the hollow attachment stud and configured to receive a nut at a free end of the hollow attachment stud; and
a plurality of standoff pins that extend from the cold side, said plurality of standoff pins surrounding the hollow attachment stud, said plurality of standoff pins forming a ring pattern around said hollow attachment stud, said ring pattern of said plurality of standoff pins defining a diameter less than a diameter of said nut,
wherein the hollow attachment stud comprises:
a cooling air passage along a central axis of said hollow attachment stud;
at least one film cooling hole penetrating through the stud end of the hollow attachment stud and configured to discharge air from the cooling air passage to a hot side of the heat shield; and
a plurality of stud cooling holes that extends through said hollow attachment stud transverse to the central axis of said hollow attachment stud, said plurality of stud cooling holes arranged along a length of said hollow attachment stud between said cold side of said heat shield and said free end of the hollow attachment stud.

4. The heat shield as recited in claim 3 , wherein said heat shield is additively manufactured.

5. The heat shield as recited in claim 3 , wherein said plurality of stud cooling holes is arranged in a radial spoke pattern.

6. The heat shield as recited in claim 3 , wherein said plurality of stud cooling holes is arranged in a spiral pattern.

7. The heat shield as recited in claim 3 , further comprising a surrounding multiple of film cooling holes through the heat shield at an angle, the at least one film cooling hole penetrating through the stud end of the hollow attachment stud arranged at the angle to align with the surrounding multiple of film cooling holes.

8. A combustor for a gas turbine engine, the combustor comprising:
a support shell having a plurality of impingement cooling holes; and
a heat shield comprising:
a hollow attachment stud connected to a cold side of the heat shield by a stud end of the hollow attachment stud;
a plurality of standoff pins extending from said cold side to abut said support shell and at least partially surrounding said hollow attachment stud, said plurality of standoff pins forming a ring pattern around said hollow attachment stud,
wherein the hollow attachment stud comprises:
a cooling air passage along a central axis of said hollow attachment stud, the hollow attachment stud extending from the cold side of said heat shield through a stud aperture in said support shell;
at least one film cooling hole penetrating through the stud end of the hollow attachment stud and configured to discharge air from the cooling air passage to a hot side of the heat shield; and
a plurality of stud cooling holes arranged transverse to, and in fluid communication with, the cooling air passage, the plurality of stud cooling holes arranged along a length of said hollow attachment stud between said cold side of said heat shield and said support shell.

9. The combustor as recited in claim 8 , further comprising a nut received onto said hollow attachment stud to retain said heat shield to said support shell.

10. The combustor as recited in claim 9 , wherein said diameter defined by said ring pattern is less than a diameter of said nut.

11. The combustor as recited in claim 9 , wherein said heat shield is additively manufactured.

12. A combustor for a gas turbine engine, the combustor comprising:
a support shell having a plurality of impingement cooling holes; and
a heat shield comprising:
a hollow attachment stud connected to a cold side of the heat shield by a stud end of the hollow attachment stud;
a plurality of standoff pins extending from said cold side to abut said support shell and surrounding said hollow attachment stud, said plurality of standoff pins forming a ring pattern around said attachment stud;
wherein the hollow attachment stud comprises:
a cooling air passage along a central axis of said hollow attachment stud, said hollow attachment stud extending from the cold side of said heat shield through a stud aperture in said support shell;
at least one film cooling hole penetrating through the stud end of the hollow attachment stud and configured to discharge air from the cooling air passage to a hot side of the heat shield; and
a plurality of stud cooling holes extending through said hollow attachment stud transverse to the central axis of said hollow attachment stud, said plurality of stud cooling holes arranged along a length of said hollow attachment stud between said cold side of said heat shield and said support shell;

wherein the heat shield further comprises at least one additional film cooling hole penetrating through said cold side within a diameter defined by said ring pattern.

13. The combustor as recited in claim 12 , wherein said plurality of stud cooling holes is arranged in a radial spoke pattern.

14. The combustor as recited in claim 12 , wherein said plurality of stud cooling holes is arranged in a spiral pattern.

15. The combustor as recited in claim 12 , wherein said plurality of stud cooling holes extends through said hollow attachment stud perpendicular to the central axis of said hollow attachment stud.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Chang Hoyt Y
• Snyder Brooks E
• Slavens Thomas N

Classifications

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title