Co-swirl orientation of combustor effusion passages for gas turbine engine combustor

Patent metadata

Field	Value
Publication number	US-10317080-B2
Application number	US-201415037484-A
Country	US
Kind code	B2
Filing date	Dec 3, 2014
Priority date	Dec 6, 2013
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

Abstract

A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.

First claim

What is claimed is:

1. A liner panel for use in a combustor for a gas turbine engine, comprising:
a forward region forward of a dilution passage, the forward region including a multiple of effusion passages each directed at a circumferential orientation relative to an axis of the gas turbine engine;
an aft region aft of the forward region, the aft region including a multiple of effusion passages each directed at an axial orientation relative to the axis; and
a forward circumferential rail forward of the forward region, wherein the orientation of the multiple of effusion passages within the forward region is parallel to the forward circumferential rail, and the orientation of the multiple of effusion passages within the aft region is perpendicular to the forward circumferential rail.

2. The liner panel as recited in claim 1 , wherein the orientation of the multiple of effusion passages within the forward region is aligned with a local swirl direction of combustion gases.

3. The liner panel as recited in claim 1 , wherein the aft region extends forward of the dilution passages by 50%-100% a diameter of the dilution passages.

4. The liner panel as recited in claim 1 , further comprising an aft circumferential rail axially downstream of the forward circumferential rail and first and second axial rails that connect the aft circumferential rail with the forward circumferential rail.

5. The liner panel as recited in claim 4 , wherein the orientation of at least one of the multiple of effusion passages is directed toward the one of the first and the second axial rails.

6. The liner panel as recited in claim 1 , wherein at least one of the multiple of effusion passages within the aft region is a singleton.

7. The liner panel as recited in claim 1 , wherein at least one of the multiple of effusion passages within the forward region is a singleton.

Assignees

• United Technologies Corp

Inventors

• Tu Jr John S
• Snyder Timothy S
• Hoke James B
• Bangerter James P
• Duhamel Dennis J
• Burns David A

Classifications

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/002

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

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title