Split-zone flow metering T-tube

Patent metadata

Field	Value
Publication number	US-9863319-B2
Application number	US-201314429167-A
Country	US
Kind code	B2
Filing date	Mar 1, 2013
Priority date	Sep 28, 2012
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

Abstract

A gas turbine engine includes a core engine that has a compressor section, a combustor section and a turbine section. A thermal management system is configured to receive a cooling stream. The thermal management system includes a metering device that is located near an outer diameter of the core engine. The metering device is configured to divide the cooling stream into multiple segregated passages. The metering device can be configured to divide the cooling stream between a first passage and a second passage that is concentric with the first passage.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a core engine including,
a compressor section,
a combustor in fluid communication with the compressor section, and
a turbine section in fluid communication with the combustor; and
a thermal management system configured to receive a cooling stream, the thermal management system including a metering device located near an outer diameter of the core engine, the metering device being configured to divide the cooling stream into multiple segregated passages, the metering device including an inner tube and an outer tube that is concentric with the inner tube, and the multiple segregated passages including a first passage defined between the outer tube and the inner tube and a second passage within the inner tube.

2. The gas turbine engine as recited in claim 1 , wherein the thermal management system is connected to the compressor section and the cooling stream is bleed air.

3. The gas turbine engine as recited in claim 1 , wherein the metering device is located at the outer diameter of the turbine section.

4. The gas turbine engine as recited in claim 1 , wherein the turbine section includes a first turbine section and a second turbine section downstream of the first turbine section, and the outer diameter is of the first turbine section.

5. The gas turbine engine as recited in claim 4 , wherein at least one of the multiple segregated passages leads to the second turbine section.

6. The gas turbine engine as recited in claim 1 , wherein at least a portion of the metering device is located radially outwards of the outer diameter relative to a central axis of the core engine.

7. The gas turbine engine as recited in claim 1 , wherein the inner tube and the outer tube extend into a radially outer end of an airfoil, through the airfoil and out from a radially inner end of the airfoil.

8. The gas turbine engine as recited in claim 1 , wherein the inner tube and the outer tube extend through an airfoil.

9. The gas turbine engine as recited in claim 1 , wherein the inner tube includes an end that is attached with an orifice plate, the orifice plate having a central opening and a plurality of orifices located circumferentially around the central opening, the plurality of orifices opening into the first passage.

10. The gas turbine engine as recited in claim 9 , further comprising a fitting mounted over the orifice plate, the fitting including a port for connecting with a cooling stream source.

11. The gas turbine engine as recited in claim 9 , wherein each of the plurality of orifices are circumferentially elongated.

12. A gas turbine engine comprising:
a core engine including,
a compressor section,
a combustor in fluid communication with the compressor section, and
a turbine section in fluid communication with the combustor, the turbine section includes a first turbine section, a second turbine section that is located downstream from the first turbine section, and a mid-turbine section axially between the first turbine and the second turbine; and

a thermal management system operable to receive a cooling stream, the thermal management system including a metering device that is configured to divide the cooling stream between a first passage leading to the mid-turbine section and a second passage that is concentric with the first passage and leading to the first turbine section.

13. The gas turbine engine as recited in claim 12 , wherein the metering device includes a plurality of orifices opening to the first passage and a central orifice opening to the second passage.

14. The gas turbine engine as recited in claim 13 , wherein the plurality of orifices are arranged circumferentially around the central orifice.

15. The gas turbine engine as recited in claim 12 , wherein the first passage is an annular passage.

16. The gas turbine engine as recited in claim 12 , wherein the metering device includes a t-shaped tube having a tube portion attached at one end to an orifice plate.

17. The gas turbine engine as recited in claim 16 , wherein the tube portion is attached at an opposed end to another tube extending coaxially therewith.

18. The gas turbine engine as recited in claim 12 , wherein the metering device is located near an outer diameter of the core engine.

19. The gas turbine engine as recited in claim 12 , wherein the first passage and the second passage extend into a radially outer end of an airfoil, through the airfoil and out from a radially inner end of the airfoil.

20. The gas turbine engine as recited in claim 12 , wherein the first turbine is on a first rotatable shaft and the second turbine is on a second, different rotatable shaft.

21. The gas turbine section as recited in claim 12 , wherein the metering device includes an inner tube and an outer tube that is concentric with the inner tube, the first passage defined between the outer tube and the inner tube and the second passage within the inner tube.

Assignees

• United Technologies Corp

Inventors

• Farah Jorge I
• Parekh Kalpendu J

Classifications

• F01D9/065

  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

• F02C3/045

  having compressor and turbine passages in a single rotor-module (F02C3/073 takes precedence) · CPC title

• F01D5/08

  Heating, heat-insulating or cooling means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title

• F01D5/18

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F02C7/18 Primary

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