Turbine scroll assembly for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11293292-B2
Application number	US-202016736199-A
Country	US
Kind code	B2
Filing date	Jan 7, 2020
Priority date	Jan 11, 2017
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

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 with a longitudinal axis comprising:
a compressor section that defines a compressor flow path;
a combustion section that includes a scroll, a scroll baffle, and a combustor, 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;
a turbine section with a turbine rotor and a turbine rotor blade shroud, the turbine rotor blade shroud including a shroud cooling passage;
a mid-frame plenum with a plenum inlet, a plenum outlet, and a plenum interior space, the mid-frame plenum fluidly connecting the compressor flow path to the scroll cooling passage, the plenum interior space configured to collect air from the compressor flow path before passage to the scroll cooling passage, the mid-frame plenum extending at least partly about the longitudinal axis in a circumferential direction, the plenum interior space disposed radially inboard of the plenum inlet and the plenum outlet, the mid-frame plenum defining a mid-frame flow path from the plenum inlet to the plenum outlet, the mid-frame flow path directed in a radially inboard direction from the plenum inlet into the plenum interior space, and in a radially outboard direction to the plenum outlet and into the scroll cooling passage;
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; and
a plurality of outlet flow control apertures that are disposed proximate an outlet of the scroll cooling passage and that are spaced apart and arranged in a circumferential direction about the longitudinal axis, the plurality of outlet flow control apertures are operable to meter the flow through the scroll cooling passage.

2. The gas turbine engine of claim 1 , further comprising a rear plenum that is fluidly connected to and downstream of the shroud cooling passage.

3. The gas turbine engine of claim 2 , further comprising a rear member disposed between the rear plenum and a collector space, the rear member including at least one opening allowing flow from the rear plenum, through the rear member, and into the collector space.

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

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

6. The gas turbine engine of claim 1 , wherein the scroll cooling passage has a generally toroidal shape with an inner diameter area and an outer diameter area, the scroll cooling passage directing flow in a toroidal direction about the scroll from the inner diameter area, toward the outer diameter area, and back toward the inner diameter area.

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

8. A gas turbine engine with a longitudinal axis comprising:
a compressor section that defines a compressor flow path;
a combustion section that includes a scroll, a scroll baffle, and a combustor, 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;
a turbine section with a turbine rotor and a turbine rotor blade shroud, the turbine rotor blade shroud including a shroud cooling passage;
a mid-frame plenum with a plenum inlet, a plenum outlet, and a plenum interior space, the mid-frame plenum fluidly connecting the compressor flow path to the scroll cooling passage, the plenum interior space configured to collect air from the compressor flow path before passage to the scroll cooling passage, the mid-frame plenum extending at least partly about the longitudinal axis in a circumferential direction, the plenum interior space disposed radially inboard of the plenum inlet and the plenum outlet, the mid-frame plenum defining a mid-frame flow path from the plenum inlet to the plenum outlet, the mid-frame flow path directed in a radially inboard direction from the plenum inlet into the plenum interior space, and in a radially outboard direction to the plenum outlet and into the scroll cooling passage;
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 scroll cooling passage being a convective cooling passage configured to convectively cool the scroll; and
the interior scroll flow path including an inlet and an outlet, the scroll including a peripheral wall that is continuous from the inlet to the outlet and that is a barrier separating the scroll cooling passage from the interior scroll flow path, the scroll baffle being continuous from the inlet to the outlet.

9. The gas turbine engine of claim 8 , further comprising a rear plenum that is fluidly connected to and downstream of the shroud cooling passage.

10. The gas turbine engine of claim 9 , further comprising a rear member disposed between the rear plenum and a collector space, the rear member including at least one opening allowing flow from the rear plenum, through the rear member, and into the collector space.

11. The gas turbine engine of claim 8 , further comprising a plurality of inlet flow control vanes disposed proximate an inlet of the scroll cooling passage, the plurality of inlet flow control vanes spaced apart and arranged in a circumferential direction about the longitudinal axis proximate the inlet of the scroll cooling passage;
wherein the plurality of inlet flow control vanes direct flow into the inlet of the scroll cooling passage.

12. A gas turbine engine with a longitudinal axis comprising:
a compressor section that defines a compressor flow path;
a combustion section that includes a scroll, a scroll baffle, and a combustor, 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;
a turbine section with a turbine rotor and a turbine rotor blade shroud, the turbine rotor blade shroud including a shroud cooling passage;
a mid-frame plenum with a plenum inlet, a plenum outlet, and a plenum interior space, the mid-frame plenum fluidly connecting the compressor flow path to the scroll cooling passage, the plenum interior space configured to collect air from the compressor flow path before passage to the scroll cooling passage, the mid-frame plenum extending at least partly about the longitudinal axis in a circumferential direction, the plenum interior space disposed radially inboard of the plenum inlet and the plenum outlet, the mid-frame plenum defining a mid-frame flow path from the plenum inlet to the plenum outlet, the mid-fram

Assignees

• Honeywell Int Inc

Inventors

• Smoke Jason
• Jan David K
• Matwey Mark

Classifications

• F01D9/023 Primary

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

• F01D9/026 Primary

  Scrolls for radial machines or engines · CPC title

• Y02T50/60

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

• F05D2220/32

  in gas turbines · CPC title

• F01D25/12

  Cooling · CPC title