Gas turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same using additive manufacturing techniques

Patent metadata

Field	Value
Publication number	US-9410702-B2
Application number	US-201414176686-A
Country	US
Kind code	B2
Filing date	Feb 10, 2014
Priority date	Feb 10, 2014
Publication date	Aug 9, 2016
Grant date	Aug 9, 2016

Abstract

Disclosed in various exemplary embodiments are turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same. In one exemplary embodiment, disclosed is a combustor for a turbine engine that includes an annular liner portion including a first metering hole positioned on a cold side annular surface of the annular liner portion and an impingement chamber positioned in the annular liner. The impingement chamber connects to an entry hole on the cold side annular surface and includes a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to an exit hole positioned on the hot side annular surface of the annular liner portion. The first metering hole is connected to the impingement chamber. The cooling air outlet passageway directs the air onto the hot side annular surface and spreads the airflow axially and laterally parallel to the hot side annular surface. Furthermore, a ratio of a radial thickness of the annular liner portion to a diameter of the entry hole is from about 2 to about 6.

First claim

What is claimed is:

1. A combustor for a turbine engine, comprising:
an annular liner portion comprising a first impingement hole positioned on a cold side annular surface of the annular liner portion; and
an impingement chamber positioned in the annular liner portion, the impingement chamber comprising a chamber entry opening and a chamber exit opening, the impingement chamber connecting to a cooling air entry opening on the cold side annular surface via the first impingement hole and connecting to a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to a cooling air exit opening positioned on the hot side annular surface of the annular liner portion, wherein the first impingement hole is connected to the impingement chamber at the chamber entry opening, wherein the cooling air outlet passageway is connected to the impingement chamber at the chamber exit opening, wherein the impingement chamber comprises an impingement surface disposed at a radially hot side end of the impingement chamber, and wherein the chamber exit opening is positioned radially outwardly toward to the cold side annular surface with respect to the impingement surface such that the chamber exit opening is disposed adjacent to a radially cold side end of the impingement chamber and is further oriented along the impingement chamber to allow cooling air to exit the impingement chamber in an axial direction,
wherein the cooling air outlet passageway is configured to allow the cooling air onto the hot side annular surface, and
wherein a ratio of a radial thickness of the annular liner portion to a diameter of the cooling air entry opening is from 2 to 6.

2. The combustor of claim 1 , wherein the impingement surface is separated from the hot side annular surface by a distance of 10 mils to 30 mils.

3. The combustor of claim 1 , wherein the first impingement hole extends for a distance of 10 mils to 30 mils from the cold side annular surface.

4. The combustor of claim 3 , wherein the first impingement hole has a cylindrical configuration with a diameter of 10 mils to 30 mils.

5. The combustor of claim 1 , wherein the chamber exit opening has a smallest cross-sectional dimension of 10 mils to 30 mils.

6. The combustor of claim 1 , further comprising turbulators or fins on the cold side annular surface.

7. The combustor of claim 1 , wherein the cooling air outlet passageway is angled at two or more angles radially with respect to the hot side annular surface.

8. The combustor of claim 1 , further comprising a second impingement chamber in fluid connection with said impingement chamber, and a cooling air inlet passageway connecting with the second impingement chamber, wherein the second impingement chamber does not have a second cooling air outlet passageway directly connected thereto.

9. The combustor of claim 1 , wherein the cooling air exit opening comprises a multi-lobed configuration or a diffusing shape.

10. A method for manufacturing a combustor for a turbine engine comprising the steps of:
generating a three-dimensional model of the combustor, the model comprising:
an annular liner portion comprising a first impingement hole positioned on a cold side annular surface of the annular liner portion; and
an impingement chamber positioned in the annular liner portion, the impingement chamber comprising a chamber entry opening and a chamber exit opening, the impingement chamber connecting to a cooling air entry opening on the cold side annular surface via the first impingement hole and connecting to a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to a cooling air exit opening positioned on the hot side annular surface of the annular liner portion, wherein the first impingement hole is connected to the impingement chamber at the chamber entry opening, wherein the cooling air outlet passageway is connected to the impingement chamber at the chamber exit opening, wherein the impingement chamber comprises an impingement surface disposed at a radially hot side end of the impingement chamber, and wherein the chamber exit opening is positioned radially outwardly toward to the cold side annular surface with respect to the impingement surface such that the chamber exit opening is disposed adjacent to a radially cold side end of the impingement chamber,
wherein the cooling air outlet passageway directs cooling air onto the hot side annular surface, and
wherein a ratio of a radial thickness of the annular liner portion to a diameter of the cooling air entry opening is from 2 to 6; and

manufacturing the combustor using direct metal laser fusion or electron beam melting in accordance with the generated three-dimensional model.

11. The method of claim 10 , wherein manufacturing comprises manufacturing using direct metal laser fusion (DMLF).

12. The method of claim 10 , wherein manufacturing comprises manufacturing using electron beam melting (EBM).

13. The method of claim 10 , further comprising subjecting the manufactured combustor to a finishing treatment.

Assignees

• Honeywell Int Inc

Inventors

• Dudebout Rodolphe
• Brandt Dustin
• Waldman David
• Neumann James
• Payne Art

Classifications

• F23R3/16 Primary

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

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title