Gas turbine engine variable porosity combustor liner

Patent metadata

Field	Value
Publication number	US-10203115-B2
Application number	US-201715627843-A
Country	US
Kind code	B2
Filing date	Jun 20, 2017
Priority date	Mar 15, 2013
Publication date	Feb 12, 2019
Grant date	Feb 12, 2019

Abstract

A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

First claim

The invention claimed is:

1. A combustor liner extending from a forward position to an aft position with respect to a gas turbine, comprising:
an outer wall extending from the forward position to the aft position and having a plurality of cold side holes projecting through the outer wall; and
an inner wall extending from the forward position to the aft position and having a plurality of hot side holes facing a combustion chamber of the gas turbine, the plurality of hot side holes projecting through the inner wall;
wherein at least one of the plurality of cold side holes or the plurality of hot side holes includes a first region of holes having a first diameter, and a second region of holes having a second diameter that is different from the first diameter; and
wherein all of the first region of holes are positioned forward of all the second region of holes;
wherein:
the second diameter is greater than the first diameter;
the at least one of the plurality of cold side holes or the plurality of hot side holes includes a third region of holes having a third diameter that is different from the first and second diameters;
the third diameter is greater than both the first diameter and the second diameter; and
the third region of holes is positioned between the first region of holes and the second region of holes.

2. The combustor liner of claim 1 , wherein the outer wall and the inner wall each include the first region of holes, the second region of holes, and the third region of holes, and wherein the outer wall and the inner wall having matching hole sizes and regions.

3. A method of forming a combustor liner extending from forward position to aft positions that are defined with respect to a gas turbine, comprising:
forming an outer wall that extends from the forward position to the aft position and includes a plurality of cold side holes projecting through the outer wall; and
forming an inner wall that extends from the forward position to the aft position and includes a plurality of hot side holes facing a combustion chamber of the gas turbine, the plurality of hot side holes projecting through the inner wall;
wherein:
one of the plurality of cold side holes or the plurality of hot side holes includes a first region of holes having a first diameter, and a second region of holes having a second diameter that is different from the first diameter;

all of the first region of holes are positioned forward of all the second region of holes;
the second diameter is greater than the first diameter;
the one of the plurality of cold side holes or the plurality of hot side holes includes a third region of holes having a third diameter that is different from the first and second diameters;
the third diameter is greater than both the first diameter and the second diameter; and
the third region of holes is positioned between the first region of holes and the second region of holes.

4. The method of claim 3 , wherein the outer wall and the inner wall each include the first region of holes, the second region of holes, and the third region of holes, and wherein the outer wall and the inner wall having matching hole sizes and regions.

5. A combustor, comprising:
an outer wall extending from a forward position to an aft position of the combustor, the outer wall having cold side holes projecting through the outer wall; and
an inner wall extending from the forward position to the aft position and having hot side holes facing a combustion chamber of the combustor, the hot side holes projecting through the inner wall;
wherein:
one of the cold side holes or the hot side holes includes a first region of holes having a first diameter, and a second region of holes having a second diameter that is different from the first diameter;

all of the first region of holes are positioned forward of all the second region of holes;
the second diameter is greater than the first diameter;
one of the cold side holes or the hot side holes includes a third region of holes;
the third region of holes have a third diameter that is greater than both the first diameter and the second diameter;
the third region of holes is positioned between the first region of holes and the second region of holes;
the outer wall and the inner wall each include the first region of holes, the second region of holes, and the third region of holes; and
the outer wall and the inner wall having matching hole sizes and regions.

6. A combustor liner extending from a forward position to an aft position with respect to a gas turbine, comprising:
an outer wall extending from the forward position to the aft position and having a plurality of cold side holes projecting through the outer wall; and
an inner wall extending from the forward position to the aft position and having a plurality of hot side holes facing a combustion chamber of the gas turbine, the plurality of hot side holes projecting through the inner wall;
wherein at least one of the plurality of cold side holes or the plurality of hot side holes includes a first region of holes having a first diameter, and a second region of holes having a second diameter that is different from the first diameter; and
wherein all of the first region of holes are positioned forward of all the second region of holes;
wherein:
the second diameter is greater than the first diameter;
the at least one of the plurality of cold side holes or the plurality of hot side holes includes a third region of holes having a third diameter that is different from the first and second diameters;
the third diameter is greater than both the first diameter and the second diameter; and
all of the first region of holes are positioned forward of the entire third region of holes.

7. The combustor liner of claim 6 , wherein the second and third regions of holes are circumferentially distributed regions about a circumference of the combustor liner, forward ends of which lie adjacent to the first region, the second and third regions extending axially rearward from the first region, and circumferentially across an arc portion in an alternating manner of the second and third regions.

8. A method of forming a combustor liner extending from forward position to aft positions that are defined with respect to a gas turbine, comprising:
forming an outer wall that extends from the forward position to the aft position and includes a plurality of cold side holes projecting through the outer wall; and
forming an inner wall that extends from the forward position to the aft position and includes a plurality of hot side holes facing a combustion chamber of the gas turbine, the plurality of hot side holes projecting through the inner wall;
wherein:
one of the plurality of cold side holes or the plurality of hot side holes includes a first region of holes having a first diameter, and a second region of holes having a second diameter that is different from the first diameter;
all of the first region of holes are positioned forward of all the second region of holes;
the second diameter is greater than the first diameter;
the one of the plurality of cold side holes or the plurality of hot side holes includes a third region of holes having a third diameter that is different from the first and second diameters;
the third diameter is greater than both the first diameter and the second diameter; and
all of the first region of holes are positioned forward of the entire third region of holes.

9. The method of claim 8 , wherein the second and third regions of holes are circumferentially distributed axial regions about a circumference of the combustor liner, forward ends of which lie adjacent to the first region, the second and third regions extending axially rear

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Pinnick Donald E
• Froemming Kenneth W
• Varney Bruce E

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• F23R3/002 Primary

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

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/005

  Combined with pressure or heat exchangers · CPC title