Turbine scroll assembly for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10655859-B2
Application number	US-201715403286-A
Country	US
Kind code	B2
Filing date	Jan 11, 2017
Priority date	Jan 11, 2017
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a compressor section that defines a compressor flow path;
a combustion section that includes a scroll, a scroll baffle, a combustor, and a combustor case, the scroll defining an interior scroll flow path, the scroll baffle surrounding at least part of the scroll to define a scroll cooling passage between the scroll baffle and the scroll, the combustor case surrounding the combustor and at least part of the scroll baffle to define a collector space between the combustor case and the scroll baffle; and
a turbine section with a turbine rotor and a turbine rotor blade shroud, the turbine rotor blade shroud including a shroud cooling passage;
the compressor section being coupled to the combustion section with the compressor flow path fluidly connected to the scroll cooling passage to direct flow from the compressor flow path along the scroll cooling passage to cool the scroll;
the combustion section being coupled to the turbine section with the scroll cooling passage fluidly connected to the shroud cooling passage to direct flow from the scroll cooling passage along the shroud cooling passage to cool the turbine rotor blade shroud;
the shroud cooling passage being fluidly connected to the collector space; and
the collector space being fluidly connected to the interior scroll flow path such that flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

2. The gas turbine engine of claim 1 , further comprising a plenum that is defined between shroud cooling passage and the collector space.

3. The gas turbine engine of claim 1 , wherein the scroll cooling passage is a convective cooling passage configured to convectively cool the scroll.

4. The gas turbine engine of claim 3 , wherein the interior scroll flow path includes an inlet and an outlet;
wherein the scroll includes a peripheral wall that is continuous and that is a barrier separating the scroll cooling passage from the interior scroll flow path.

5. The gas turbine engine of claim 1 , wherein the scroll cooling passage directs flow in a toroidal direction about the scroll.

6. The gas turbine engine of claim 1 , further comprising a mid-frame plenum that is disposed between the compressor flow path and the scroll cooling passage.

7. The gas turbine engine of claim 1 , wherein the combustion section defines a longitudinal axis;
further comprising an inlet flow control member disposed proximate an inlet of the scroll cooling passage, the inlet flow control member including a plurality of vanes that are spaced apart and arranged in a circumferential direction about the longitudinal axis proximate the inlet of the scroll cooling passage;
wherein the plurality of vanes direct flow into the inlet of the scroll cooling passage.

8. The gas turbine engine of claim 1 , wherein the combustion section defines a longitudinal axis;
further comprising an outlet flow control member disposed proximate an outlet of the scroll cooling passage;
wherein the outlet flow control member is operable to meter the flow through the scroll cooling passage.

9. The gas turbine engine of claim 1 , wherein the combustor case at least partly defines a plenum that receives flow from the scroll cooling passage;
further comprising a rear member disposed between the plenum and the collector space, the rear member including at least one opening allowing flow from the plenum, through the rear member, and into the collector space.

10. A component for a gas turbine engine comprising:
a scroll with a scroll peripheral wall having an inner surface and an outer surface, the inner surface defining an interior scroll flow path that extends generally in a circumferential direction about a longitudinal axis;
a scroll baffle that surrounds at least part of the scroll, the scroll baffle including a baffle peripheral wall having an inner surface and an outer surface, the inner surface of the baffle peripheral wall facing the outer surface of the scroll peripheral wall; and
a scroll cooling passage defined between the outer surface of the scroll peripheral wall and the inner surface of the baffle peripheral wall, the scroll cooling passage including an inlet and an outlet and having a generally toroidal shape with an inner diameter area and an outer diameter area, the scroll cooling passage configured to direct a flow from the inlet to the outlet in a toroidal direction about the scroll from the inner diameter area, toward the outer diameter area, and back toward the inner diameter area to cool the scroll;
the scroll peripheral wall being continuous along the scroll cooling passage between the inlet and the outlet, the scroll peripheral wall blocking the flow from entering the interior scroll flow path; and
the baffle peripheral wall being continuous along the scroll cooling passage between the inlet and the outlet.

11. The component of claim 10 , further comprising a turbine section with a turbine rotor and a turbine rotor blade shroud, the turbine rotor blade shroud including a shroud cooling passage;
wherein at least one of the scroll and the scroll baffle are attached to the turbine rotor blade shroud to fluidly connect the outlet of the scroll cooling passage to the shroud cooling passage;
wherein the shroud cooling passage is configured to receive the flow from the scroll cooling passage to cool the turbine rotor blade shroud.

12. The component of claim 10 , wherein the scroll cooling passage is a convective cooling passage configured to convectively cool the scroll.

13. The component of claim 10 , wherein the scroll peripheral wall defines an outlet of the interior scroll flow path, the outlet being disposed on an inner diameter area of the scroll;
wherein the scroll baffle includes a first member and a second member that cooperate to surround at least part of the scroll, an opening defined in the scroll baffle that provides fluid access for the flow from the outlet of the interior scroll flow path to be directed toward a turbine rotor.

14. The component of claim 13 , wherein the first member covers over a front end of the scroll, wherein the second member covers over a rear end of the scroll, and wherein the first member and the second member are attached at a junction;
wherein the junction extends in the circumferential direction about the scroll baffle.

15. The component of claim 10 , wherein the scroll peripheral wall defines an inlet of the interior scroll flow path;
wherein the baffle peripheral wall encompasses the inlet;
wherein the baffle peripheral wall is attached to the scroll peripheral wall and closes off the scroll cooling passage proximate the inlet.

16. A component for a gas turbine engine comprising:
a combustor and a combustor case;
a scroll with a scroll peripheral wall having an inner surface and an outer surface, the inner surface defining an interior scroll flow path that extends generally in a circumferential direction about a longitudinal axis;
a scroll baffle that surrounds at least part of the scroll, the scroll baffle including a baffle peripheral wall having an inner surface and an outer surface, the inner surface of the baffle peripheral wall facing the outer surface of the scroll peripheral wall, the combustor case surrounding the combustor and at least part of the scroll baffle to define a collector space between the combustor case and the scroll baffle;
a scroll cooling passage defined between the outer surface of the scroll peripheral wall and the inner surface of the baffle peripheral wall, the scroll cooling pa

Assignees

• Honeywell Int Inc

Inventors

• Smoke Jason
• Jan David K
• Matwey Mark

Classifications

• F23R3/52

  Toroidal combustion chambers · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D9/026 Primary

  Scrolls for radial machines or engines · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title