Turbine engine with metered cooling system

Patent metadata

Field	Value
Publication number	US-11434775-B2
Application number	US-202017007639-A
Country	US
Kind code	B2
Filing date	Aug 31, 2020
Priority date	Aug 31, 2020
Publication date	Sep 6, 2022
Grant date	Sep 6, 2022

Abstract

An assembly adapted for use with a gas turbine engine includes a static component and a metering band. The static component is fixed relative to an axis. The metering band is arranged to extend circumferentially at least partway about the axis and is coupled with the static component. The metering band defines at least a portion of a cooling passageway for air to flow through.

First claim

What is claimed is:

1. An assembly adapted for use with a gas turbine engine, the assembly comprising
a static component fixed relative to an axis,
a first metering band arranged to extend circumferentially at least partway about the axis and coupled with the static component at a discrete location, and
a second metering band located adjacent the first metering band and arranged to extend circumferentially at least partway about the axis and coupled with the static component,
wherein the first metering band defines at least a portion of a cooling passageway, the second metering band defines another portion of the cooling passageway, and the first metering band is configured to expand and contract relative to the static component in response to temperature changes of the assembly to change a size of the cooling passageway,
wherein the first metering band extends in a first circumferential direction about the axis from a first terminal end to a second terminal end of the first metering band, the second metering band extends in a second circumferential direction, opposite the first circumferential direction, from a first terminal end to a second terminal end of the second metering band, and the first terminal end of the first metering band and the first terminal end of the second metering band are fixed to the static component.

2. The assembly of claim 1 , wherein the second metering band is located axially adjacent the first metering band.

3. The assembly of claim 1 , wherein the first metering band has a first coefficient of thermal expansion, the second metering band has a second coefficient of thermal expansion, and the first coefficient of thermal expansion is different from the second coefficient of thermal expansion.

4. The assembly of claim 1 , wherein the first metering band is formed to define a first aperture that extends through the first metering band, the second metering band is formed to define a second aperture that extends through the second metering band, and the cooling passageway is defined by the first aperture and the second aperture.

5. The assembly of claim 4 , wherein the first aperture extends axially through the first metering band and the second aperture extends axially through the second metering band.

6. The assembly of claim 1 , wherein the first metering band extends circumferentially between the first terminal end and the second terminal end and the second terminal end is free to move relative to the first terminal end.

7. The assembly of claim 1 , wherein the first metering band includes a first segment having a first radial thickness and a second segment having a second radial thickness greater than the first radial thickness and the second segment is formed to include a plurality of apertures that extend axially though the first metering band.

8. The assembly of claim 1 , wherein the first metering band is a full annular hoop formed to include a plurality of circumferential slots that extend axially through the first metering band.

9. An assembly adapted for use with a gas turbine engine, the assembly comprising
a static component fixed in position relative to an axis, the static component formed to define a channel that extends circumferentially around the axis,
a first metering band located in the channel and arranged to extend circumferentially at least partway about the axis, and the first metering band coupled to the static component at a first discrete location for movement with the static component,
a second metering band located in the channel and arranged to extend circumferentially at least partway about the axis, the second metering band located adjacent the first metering band, and the second metering band coupled to the static component at a second discrete location for movement with the static component,
wherein the first metering band and the second metering band cooperate to define a cooling passageway and the first metering band and the second metering band are configured to expand and contract relative to the static component in response to temperature changes of the assembly to change a size of the cooling passageway,
wherein the first metering band extends in a first circumferential direction about the axis from a first terminal end to a second terminal end of the first metering band, the second metering band extends in a second circumferential direction, opposite the first circumferential direction, from a first terminal end to a second terminal end of the second metering band, and the first terminal end of the first metering band and the first terminal end of the second metering band are fixed to the static component.

10. The assembly of claim 9 , wherein the first metering band is formed to include a first aperture that extends through the first metering band, the second metering band is formed to include a second aperture that extends through the second metering band, and an overlap of the first aperture and the second aperture is configured to vary in response to the temperature changes of the assembly to change the size of the cooling passageway.

11. The assembly of claim 10 , wherein the first aperture extends axially through the first metering band and the second aperture extends axially through the second metering band.

12. The assembly of claim 11 , wherein the first metering band extends circumferentially between the first terminal end and the second terminal end and the second terminal end is free to move relative to the first terminal end.

13. The assembly of claim 12 , wherein the first metering band includes a thermal expansion ring having a first radial thickness and an aperture ring having a second radial thickness greater than the first radial thickness, and the first aperture is formed in the aperture ring.

14. The assembly of claim 13 , wherein the first metering band extends circumferentially about the axis greater than 360 degrees from the first terminal end to the second terminal end.

15. The assembly of claim 9 , wherein the first metering band has a first coefficient of thermal expansion, the second metering band has a second coefficient of thermal expansion, and the first coefficient of thermal expansion is different from the second coefficient of thermal expansion.

16. The assembly of claim 9 , wherein the first metering band is a full annular hoop formed to include a plurality of circumferential slots that extend axially through the first metering band and the second metering band is a full annular hoop formed to include a plurality of circumferential slots that extend axially through the second metering band.

17. A method for varying cooling flow in a gas turbine engine, the method comprising the steps of:
mounting a first metering band to a static component so that a first terminal end of the first metering band is fixed at a discrete location of the static component and a second terminal end of the first metering band is free to move relative to the first terminal end, and an aperture that extends through the first metering band forms a portion of a cooling passageway,
arranging a first aperture that extends through in the first metering band to form a portion of a cooling passageway to overlap with a second aperture that extends through the static component that forms another portion of the cooling passageway to form a cooling passage area,
varying a circumferential length of the first metering band so that the second terminal end extends away from and toward the first terminal end in response to temperature changes of the gas turbine engine so that the first aperture and the second aperture move

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Snyder Brandon R
• Sands Jonathan S

Classifications

• F01D9/065 Primary

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D9/06 Primary

  Fluid supply conduits to nozzles or the like · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title

• F01D17/14

  varying effective cross-sectional area of nozzles or guide conduits · CPC title