Fuel lance cooling for a gas turbine with sequential combustion

Patent metadata

Field	Value
Publication number	US-10920985-B2
Application number	US-201514947701-A
Country	US
Kind code	B2
Filing date	Nov 20, 2015
Priority date	Nov 20, 2014
Publication date	Feb 16, 2021
Grant date	Feb 16, 2021

Abstract

A fuel lance is disclosed for injecting a gaseous and/or liquid fuel mixed with air into an axial hot gas flow flowing through a sequential combustor of a gas turbine, the fuel lance having at least one finger extending in a longitudinal direction into the axial hot gas flow of the gas turbine essentially perpendicular to the hot gas flow. The finger is configured as a streamlined body which has a streamlined cross-sectional profile. The body has two lateral surfaces essentially parallel to the axial hot gas flow. The body includes an enclosing outer wall having a longitudinally extending air plenum for the distributed introduction of air into the at least one finger. The air plenum is provided with a plurality of distributed impingement cooling holes, such that air exiting through the impingement cooling holes impinges on the inner side of the leading edge region of the body.

First claim

The invention claimed is:

1. A fuel lance for injecting a gaseous and/or a liquid fuel and air into an axial hot gas flow flowing through a sequential combustor of a gas turbine, said fuel lance comprising:
at least one finger extending into said axial hot gas flow in a longitudinal direction that is perpendicular to said axial hot gas flow,
wherein said at least one finger is configured as a streamlined body which has a streamlined cross-sectional profile,
wherein said streamlined body has two lateral surfaces arranged to be parallel to said axial hot gas flow, joined at their upstream side by a leading edge and joined at their downstream side forming a trailing edge,
wherein a plurality of nozzles are distributed along said trailing edge,
wherein means for impacting a mixing quality and reducing pressure loss in said sequential combustor are provided at a region around the trailing edge of said streamlined body,
wherein said streamlined body includes an enclosing outer wall defining said streamlined cross-sectional profile,
wherein within said enclosing outer wall there is provided a longitudinally extending air plenum for a distributed introduction of the air into said at least one finger, said longitudinally extending air plenum having a first distance from said enclosing outer wall, defining a first interspace,
wherein said longitudinally extending air plenum is provided with a plurality of distributed impingement cooling holes, such that the air exiting through said plurality of distributed impingement cooling holes impinges on an inner side of the enclosing outer wall at a region around the leading edge of said streamlined body, wherein the air is mixed with the gaseous and/or the liquid fuel after exiting through the plurality of distributed impingement cooling holes,
wherein said plurality of distributed impingement cooling holes each have a hole diameter between 1.2 mm and 1.8 mm, and said plurality of distributed impingement cooling holes are arranged at said longitudinally extending air plenum with a first pitch ratio, the first pitch ratio being a distance between two holes of said plurality of distributed impingement cooling holes and the hole diameter of any one of the two holes and being between 3 and 10,
wherein a height of the first interspace between said longitudinally extending air plenum and said enclosing outer wall perpendicular to said enclosing outer wall increases beginning from said leading edge towards said trailing edge of said streamlined body,
wherein within said enclosing outer wall there is provided a longitudinally extending gas plenum for a distributed introduction of the gaseous fuel into said at least one finger, said longitudinally extending gas plenum being arranged in a middle between said leading edge and said trailing edge with a second distance from said enclosing outer wall, defining a second interspace,
wherein a plurality of distributed pin fins are arranged on the inner side of said enclosing outer wall of said streamlined body at a region around said longitudinally extending gas plenum for convective cooling of said enclosing outer wall by the air flowing from said longitudinally extending air plenum to said region around the trailing edge through said second interspace between said longitudinally extending gas plenum and said enclosing outer wall, wherein the plurality of distributed pin fins are entirely downstream of said first interspace with respect to the air flowing from said longitudinally extending air plenum to said region around the trailing edge.

2. The fuel lance according to claim 1 , wherein said plurality of distributed pin fins have a height perpendicular to said enclosing outer wall between 1.5 mm and 2.5 mm, and said plurality of distributed pin fins have a second pitch ratio, the second pitch ratio being a ratio of distance between two pin fins of the plurality of distributed pin fins and a diameter of one of the two pin fins, and being between 3 and 5.

3. The fuel lance according to claim 2 , wherein said plurality of distributed pin fins are cylindrical or tapered or hoof-shaped or teardrop shaped.

4. The fuel lance according to claim 2 , wherein a plurality of distributed effusion cooling holes are provided in said enclosing outer wall at the region around the trailing edge, through which the air from said longitudinally extending air plenum exits said streamlined body after having convectively cooled said enclosing outer wall in said second interspace.

5. The fuel lance according to claim 1 , wherein said means for impacting the mixing quality and reducing the pressure loss in said sequential combustor comprises:
a plurality of vortex generators arranged on said streamlined body on both sides at the region around the trailing edge.

6. Fuel lance according to claim 1 , wherein said means for impacting the mixing quality and reducing the pressure loss in said sequential combustor comprises: lobes being arranged between said nozzles at the trailing edge of said streamlined body.

7. The fuel lance according to claim 1 , wherein said fuel lance is configured for a rectangular burner.

8. Fuel lance according to claim 1 , wherein said fuel lance is configured for a center-body burner.

9. The fuel lance according to claim 1 , wherein increasing the height of the first interspace allows a reduction of cross flow velocity and an enhancement of impingement cooling efficiency downstream.

10. The fuel lance according to claim 5 , wherein each vortex generator of said plurality of vortex generators comprises:
a leading panel, and guiding ribs to guide an air flow closer to said leading panel.

11. The fuel lance according to claim 10 , comprising: a flow separator in a longitudinal middle of said longitudinally extending air plenum to separate said air flowing from both ends of the longitudinally extending air plenum and to avoid instabilities.

12. The fuel lance according to claim 1 , wherein a bypass is provided at said longitudinally extending air plenum through which bypass air flows from said longitudinally extending air plenum into said second interspace.

13. The fuel lance according to claim 1 , wherein release holes are provided in the enclosing outer wall at a downstream end of said longitudinally extending gas plenum to avoid a dead air flow corner behind said longitudinally extending gas plenum.

14. The fuel lance according to claim 5 , wherein said vortex generators are made of a ceramic.

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Gao Xianfeng
• Benz Urs
• Theuer Andre
• Düsing Michael

Classifications

• F23R3/16

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

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title

• Y02T50/60

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

• F23R3/20

  incorporating fuel injection means · CPC title

• F23R3/18

  Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants · CPC title