Gas turbine transition duct

Patent metadata

Field	Value
Publication number	US-10787918-B2
Application number	US-201715680378-A
Country	US
Kind code	B2
Filing date	Aug 18, 2017
Priority date	Aug 22, 2016
Publication date	Sep 29, 2020
Grant date	Sep 29, 2020

Abstract

A gas turbine transition duct includes: an inner tubular body, defining a transition channel and having a first upstream end and a first downstream end for coupling to a can combustor and to a turbine section of a gas turbine assembly, respectively; an outer tubular body, arranged around the inner tubular body and having a second upstream end at the first upstream end of the inner tubular body and a second downstream end at the first downstream end of the inner tubular body; wherein a convective cooling channel is defined between the inner tubular body and the outer tubular body, the convective cooling channel having an inlet between the first downstream end and the second downstream end; and wherein the outer tubular body is continuous between the second upstream end and the second downstream end.

First claim

The invention claimed is:

1. A gas turbine transition duct comprising:
an inner tubular body, defining a transition channel and having a first upstream end and a first downstream end for coupling to a can combustor and to a turbine section of a gas turbine assembly, respectively;
an outer tubular body, arranged around the inner tubular body and having a second upstream end at the first upstream end of the inner tubular body and a second downstream end at the first downstream end of the inner tubular body; wherein a convective cooling channel is defined between the inner tubular body and the outer tubular body, the convective cooling channel having an inlet between the first downstream end and the second downstream end; and
wherein the outer tubular body is continuous between the second upstream end and the second downstream end,
wherein the inner tubular body has i) an annular rib that extends in a radially outward direction, the annular rib having a flat face and on a side opposite the flat face, a curved concave face connected to the convective cooling channel for guiding a cooling flow to the convective cooling channel and ii) a portion that extends in a direction downstream of the annular rib; and iii) a first frame at the first downstream end, wherein the portion of the inner tubular body extends through the first frame such that the first frame abuts the flat face and surrounds said portion.

2. The transition duct according to claim 1 , wherein the convective cooling channel is configured to convey the cooling flow along an outer surface of the inner tubular body from the first downstream end and second downstream end towards the first upstream end and second upstream end.

3. The transition duct according to claim 2 , wherein the convective cooling channel extends all around the inner tubular body, the inlet defines an inlet flow direction transverse to the outer surface of the inner tubular body at all sides of the inner tubular body and the inlet is configured to guide the cooling flow along the outer surface of the inner tubular body.

4. The transition duct according to claim 2 , wherein:
the outer tubular body has a second frame at the second downstream end, the second frame being arranged parallel to and at a distance from the first frame; and
the inlet of the convective cooling channel is defined between the first frame and the second frame.

5. The transition duct according to claim 4 , comprising:
a splitter in the inlet of the convective cooling channel.

6. The transition duct according to claim 5 , wherein the splitter comprises:
a third frame, arranged between the first frame and the second frame.

7. The transition duct according to claim 5 , wherein the splitter has an edge bent to guide the cooling flow along the outer surface of the inner tubular body.

8. The transition duct according to claim 4 , comprising:
spacers between the first frame and the second frame, the spacers being set across the inlet of the convective cooling channel.

9. The transition duct according to claim 8 , wherein the second frame is secured to the first frame by fasteners that extend through respective spacers.

10. A gas turbine assembly comprising:
a compressor section, extending along a main axis;
a plurality of can combustors, circumferentially arranged about the main axis;
a turbine section;
at least one transition duct according to claim 1 .

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Marlow Paul
• Maurer Michael
• Vrbetic Dalibor

Classifications

• F23R3/42

  characterised by the arrangement or form of the flame tubes or combustion chambers · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F02C7/222 Primary

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

• F01D9/023 Primary

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title