Combustor with improved swirl

• US 7,628,020 B2
• Filed: 05/26/2006
• Issued: 12/08/2009
• Est. Priority Date: 05/26/2006
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Morenko, Oleg, Alkabie, Hisham, McCaldon, Kian
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): Wongwian; Phutthiwat
• Application Number:
  US11/441,223
• Publication Number:
  US 20070271925A1
• Time in Patent Office: 1,292 Days
• Field of Search: 607/52, 608/04
• US Class Current: 60/752
• CPC Class Codes: F23R 2900/03041 Effusion cooled combustion chamber walls or domes
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52
• CPC Class Codes: F23R 3/54 Reverse-flow combustion chambers

Abstract

A combustor having a combustor wall with a plurality of angled effusion holes defined therethrough. The tangential component of the hole direction of the effusion holes corresponds to a same rotational direction about the central axis of the combustor. The effusion holes directional arrangement is angled from a radial plane and the combustor liner surfaces in order to promote swirl at the combustor exit.

Claims

1. A combustor comprising inner and outer liners extending longitudinally from a dome wall about the central axis of the combustor to define an annular enclosure therebetween, the inner and outer liners having a plurality of angled effusion holes defined therethrough, each of the effusion holes having a hole direction defined along a central axis thereof and toward the enclosure, the hole direction of each of the effusion holes having a tangential component defined tangentially to a corresponding one longitudinally extending section of the inner and outer liners and perpendicularly to the central axis of the combustor, the tangential component of all of the effusion holes corresponding to a same rotational direction about the central axis of the combustor to swirl a flow coming in the enclosure through the effusion holes along the same rotational direction, wherein the inner and outer liners define first and second longitudinally extending annular sections of the annular enclosure with the first section being adapted to receive a plurality of fuel nozzles and the second section being located downstream of the first section, the hole direction of each of the effusion holes, in a radial plane having a longitudinal component defined tangentially to the corresponding one of the liners, and wherein the longitudinal component of each of the effusion holes in the first section of the outer liner is directed away from the second section towards the dome wall and the longitudinal component of each of the effusion holes defined in the second section of the outer liner is directed away from the first section and the dome wall.

2. The combustor as defined in claim 1, wherein the hole direction of each of the effusion holes forms an angle having an absolute value of between 20 and 30 degrees with the corresponding one of the liners.

3. The combustor as defined in claim 1, wherein a projection of the hole direction of each of the effusion holes on an outer surface of the corresponding one of the liners forms an angle having an absolute value of approximately 45 degrees with a corresponding radial plane extending radially from the axis of the combustor.

4. The combustor as defined in claim 1, wherein for the inner liner the longitudinal component of each of the effusion holes defined in the first section is directed toward the second section and the longitudinal component of each of the effusion holes defined in the second section is directed away from the first section.

5. A combustor comprising inner and outer liners defining an annular enclosure therebetween, the inner and outer liners having a plurality of angled effusion holes defined therethrough, each of said effusion holes intersecting a corresponding imaginary radial plane extending radially from a central axis of the combustor, each of a plurality of the effusion holes extending at a first angle with respect to a corresponding one of the liners and at a second angle with respect to the corresponding radial plane, the effusion holes directing a flow coming therethrough along a same rotational direction about the central axis, wherein the outer liner has effusion holes with opposite longitudinal components, wherein the inner and outer liners define first and second longitudinally extending annular sections relative to a dome end wall of the annular enclosure, the first section being adapted to receive a plurality of fuel nozzles and the second section being located downstream of the first section, the effusion holes being defined through the inner and outer liners in the first and second sections, the first angle of each of the effusion holes being acute and measured from the corresponding one of the liners with a first orientation, the second angle of each of the effusion holes being acute and measured from the corresponding radial plane with a second orientation, and wherein the first and second orientations of the effusion holes defined in the first section and wherein the first and second orientations of the effusion holes defined in the first section of the outer liner are opposite respectively to the first and second orientations of the effusion holes defined in the second section of the outer liner.

6. The combustor as defined in claim 5, wherein each of the effusion holes extend perpendicularly to the corresponding radial plane, the inner and outer liners having additional effusion holes defined therethrough, each of the additional effusion holes extending at an angle with respect to a corresponding one of the liners and parallel to a corresponding radial plane extending radially from the central axis of the combustor.

7. The combustor as defined in claim 5, wherein the first angle has an absolute value of between 20 and 30 degrees.

8. The combustor as defined in claim 5, wherein a projection of the second angle on an outer surface of the corresponding one of the liners has an absolute value of approximately 45 degrees.

9. The combustor as defined in claim 5, wherein for the inner liner the first and second orientations of the effusion holes defined in the first section are the same respectively as the first and second orientations of the effusion holes defined in the second section.