Minicore cooling passage network having sloped impingement surface

Patent metadata

Field	Value
Publication number	US-11149556-B2
Application number	US-201916667949-A
Country	US
Kind code	B2
Filing date	Oct 30, 2019
Priority date	Nov 9, 2018
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.

First claim

What is claimed is:

1. A gas turbine engine article comprising:
an article wall defining a cavity; and
a cooling passage network embedded in the article wall between inner and outer portions of the article wall, the cooling passage network having an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, a sub-passage region including a plurality of sub-passages, at least one outlet orifice through the outer portion of the article wall that is connected to the sub-passage region, and a manifold region having a plenum upstream of the sub-passage region, the manifold region including a delivery passage connecting the inlet orifice to the plenum, the delivery passage diverging in size from the inlet orifice,
the outer portion of the article wall having a sloped impingement surface located opposite the inlet orifice in the cooling passage network, the sloped impingement surface being angled to divert flow of cooling air from the inlet orifice toward the plenum.

2. The article as recited in claim 1 , wherein the inlet orifice defines a central axis, and there is an angle in the cooling passage network that opens toward the plenum that is subtended by the central axis and the sloped impingement surface, and the angle is greater than 90°.

3. The article as recited in claim 2 , wherein the angle is greater than or equal to 110°.

4. The article as recited in claim 2 , wherein the angle is less than or equal to 160°.

5. The article as recited in claim 1 , wherein the angle is from 100° to 135°.

6. The article as recited in claim 1 , wherein the sloped impingement surface is non-faceted.

7. The article as recited in claim 1 , wherein the divergence in size in in a radial direction.

8. The article as recited in claim 1 , wherein the sub-passage region includes a plurality of pedestals that define the sub-passages, and there is additionally an exit region between the sub-passage region and the at least one outlet orifice, the exit region having a plurality of flow guides.

9. A gas turbine engine article comprising:
an article wall defining a cavity; and
a cooling passage network embedded in the article wall between inner and outer portions of the article wall, the cooling passage network having first and second inlet orifices through the inner portion of the article wall to receive cooling air from the cavity, a sub-passage region including a plurality of sub-passages, at least one outlet orifice through the outer portion of the article wall that is connected to the sub-passage region, a manifold region having a plenum upstream of the sub-passage region, and first and second delivery passages connecting, respectively, the first and second inlet orifices to the plenum, the first and second delivery passages diverging in size from the respective first and second inlet orifices.

10. The article as recited in claim 9 , wherein the size that is diverging is a radial size.

11. The article as recited in claim 10 , wherein the radial size diverges at an angle of 10° to 60°.

12. The article as recited in claim 11 , wherein the radial size diverges at an angle of 25° to 50°.

13. The article as recited in claim 9 , wherein the plenum includes at least one flow guide.

14. The article as recited in claim 9 , wherein the outer portion of the article wall has a sloped impingement surface opposite the first and second inlet orifices to divert flow of cooling air toward the plenum.

15. A gas turbine engine comprising:
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 having a gas turbine engine article that includes
an article wall defining a cavity,
a cooling passage network embedded in the article wall between inner and outer portions of the article wall, the cooling passage network having an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, a plurality of sub-passages that extend axially from the at least one inlet orifice, at least one outlet orifice through the outer portion of the article wall, and a manifold region having a plenum upstream of the plurality of sub-passages, the manifold region including at least one delivery passage connecting the at least one inlet orifice to the plenum, the at least one delivery passage diverging in size from the at least one inlet orifice, and
the outer portion of the article wall having a sloped impingement surface located opposite the at least one inlet orifice in the cooling passage network, the sloped impingement surface being angled to divert flow of cooling air from the at least one inlet orifice toward the sub-passages.

16. The gas turbine engine as recited in claim 15 , wherein the at least one inlet orifice defines a central axis, and there is an angle in the cooling passage network that opens toward the plenum that is subtended by the central axis and the sloped impingement surface, and the angle is from 100° to 160°.

17. The gas turbine engine as recited in claim 15 , wherein the at least one delivery passage diverges in radial size from the inlet orifice, and the sloped impingement surface is non-faceted.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Paauwe Corneil S
• Propheter-Hinckley Tracy A
• Arisi Allan N

Classifications

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D9/023

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

• F23R3/005

  Combined with pressure or heat exchangers · CPC title