Gas turbine engine turbine impeller pressurization

Patent metadata

Field	Value
Publication number	US-10072585-B2
Application number	US-201414769591-A
Country	US
Kind code	B2
Filing date	Mar 10, 2014
Priority date	Mar 14, 2013
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

First claim

What is claimed is:

1. A cooling system for a gas turbine engine turbine section, comprising:
a rotor supporting a blade having a cooling passage;
a disc secured relative to the rotor and forming a cavity between the rotor and the disc;
a bleed air source in fluid communication with the cavity;
an impeller is arranged in the cavity and configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage, wherein the bleed air source is a stage of a high pressure compressor section, the high pressure compressor section includes an aft hub having an aft hub leak path, the aft hub leak path in fluid communication with the cavity and configured to provide aft hub fluid to the cavity; and
a tangential on board injector having a TOBI leak path, the TOBI leak path in fluid communication with the cavity and configured to provide a TOBI fluid to the cavity.

2. The cooling system according to claim 1 , wherein the blade is in a last stage of a high pressure turbine section.

3. The cooling system according to claim 2 , comprising a spool, the rotor and the disc affixed to the spool for rotation therewith.

4. The cooling system according to claim 1 , wherein the impeller is mounted on the disc.

5. The cooling system according to claim 4 , wherein the impeller includes circumferentially spaced paddles integral with disc.

6. The cooling system according to claim 1 , comprising static structure, and the disc includes a seal configured to seal relative to the static structure.

7. The cooling system according to claim 1 , wherein the impeller includes a set of first paddles and a set of second paddles, the first and second paddles interleaved relative to one another, the first paddles larger than the second paddles.

8. The cooling system according to claim 1 , wherein rotor supports turbine blades having a cooling passage in fluid communication with the cavity, and the disc includes a seal in engagement with turbine blades.

9. The cooling system according to claim 8 , wherein the disc includes an annular flange providing the seal, the annular flange extending in an axial direction and spaced radially from the sets of first and second paddles to provide an annular channel radially between the annular flange and the sets of first and second paddles.

10. The cooling system according to claim 7 , wherein a disc-shaped wall supports the set of first and second paddles that extend from an inlet radially outward to an outlet, an annular flange extending axially from the wall to provide an annular channel arranged radially between the outlet and the annular flange.

11. The disc according to claim 10 , comprising a second seal supported by the wall on a side opposite the paddles.

Assignees

• United Technologies Corp

Inventors

• Mosley John H
• Chrisikos James P
• O'Connor John J
• Wu Charles C
• Glasspoole David
• Gates Roger

Classifications

• F05D2220/3215

  the last stage of the turbine · CPC title

• F01D5/082 Primary

  on the side of the rotor disc · CPC title

• F02C7/18

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

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• Y02T50/676

  Cross-Sectional Technologies · mapped topic