S-shaped trip strips in internally cooled components

Patent metadata

Field	Value
Publication number	US-10156157-B2
Application number	US-201514622062-A
Country	US
Kind code	B2
Filing date	Feb 13, 2015
Priority date	Feb 13, 2015
Publication date	Dec 18, 2018
Grant date	Dec 18, 2018

Abstract

A component for a gas turbine engine is provided. The component includes an internal cooling passage disposed within the component, and an s-shaped trip strip formed on a surface of the internal cooling passage.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, comprising:
an internal cooling passage disposed within the airfoil;
an opposing set of s-shaped trip strips formed on opposing surfaces of the internal cooling passage and extending spanwise along at least 75% of an airfoil span as measured between an airfoil root and an airfoil tip of the airfoil;
each of the opposing set of s-shaped trip strips comprising a peak, a trough, a first middle segment, and a second middle segment, wherein the peak and the trough defines a contour having smooth or repetitive oscillations, wherein each of the opposing set of s-shaped trip strips extend partially into the interior of the internal cooling passage from a respective surface of the internal cooling passage toward an opposing surface of the internal cooling passage and terminates prior to contacting the opposing surface of the internal cooling passage;
and each of the opposing set of s-shaped trip strips further comprising a first linear trip strip formed on the respective surface of the internal cooling passage proximate an s-shaped trip strip, wherein the first linear trip strip extends in an aft direction from an area defined between the first middle segment and the second middle segment and proximate one of the peak or the trough.

2. The airfoil of claim 1 , further comprising a second linear trip strip formed on the respective surface of the internal cooling passage and extending in a forward direction away from the s-shaped trip strip.

3. The component of claim 1 , wherein the s-shaped trip strip is off-center relative to the respective surface of the internal cooling passage.

4. The airfoil of claim 1 , wherein the s-shaped trip strip is continuous.

5. The component of claim 1 , wherein the s-shaped trip strip is broken.

6. The airfoil of claim 1 , further comprising a second internal cooling passage in fluid communication with the s-shaped trip strip.

7. A gas turbine engine, comprising:
a compressor;
an internally cooled airfoil aft of the compressor comprising a cooling passage;
an opposing set of serpentine trip strips disposed on opposing surfaces of the cooling passage and extending spanwise along at least 75% of an airfoil span as measured between an airfoil root and an airfoil tip of the internally cooled airfoil;
each of the opposing set of serpentine trip strips comprising a peak, a trough, a first middle segment, and a second middle segment, wherein the peak and the trough defines a contour having smooth or repetitive oscillations, wherein each of the opposing set of serpentine trip strips extends partially into the interior of the cooling passage from a respective surface of the cooling passage toward the opposing surface of the cooling passage and terminates prior to contacting the opposing surface of the cooling passage, and each of the opposing set of serpentine trip strips further comprising a first linear trip strip formed on the respective surface of the internal cooling passage proximate a serpentine trip strip, wherein the first linear trip strip extends in an aft direction from an area defined between the first middle segment and the second middle segment and proximate one of the peak or the trough.

8. The gas turbine engine of claim 7 , wherein the compressor is configured to deliver coolant to the cooling passage.

9. The gas turbine engine of claim 7 , further comprising a second linear trip strip formed on the respective surface of the cooling passage and extending in a forward direction away from the serpentine trip strip.

10. The gas turbine engine of claim 7 , wherein the serpentine trip strip is off-center relative to the respective surface of the cooling passage.

11. The gas turbine engine of claim 7 , wherein the serpentine trip strip is continuous.

12. The gas turbine engine of claim 7 , wherein the serpentine trip strip is broken.

13. The gas turbine engine of claim 7 , further comprising a second internal cooling passage in fluid communication with the serpentine trip strip.

14. The gas turbine engine of claim 7 , wherein the internally cooled airfoil comprises an airfoil.

15. An internally cooled airfoil, comprising:
an internal cooling passage; and
an opposing set of s-shaped trip strips formed on opposing surfaces of the internal cooling passage and extending spanwise along at least 75% of an airfoil span as measured between an airfoil root and an airfoil tip of the internally cooled airfoil;
each of the opposing set of s-shaped trip strips comprising a peak, a trough, a first middle segment, and a second middle segment, wherein the peak and the trough defines a contour having smooth or repetitive oscillations, wherein each of the opposing set of s-shaped trip strips extend partially into the interior of the internal cooling passage from a respective surface of the internal cooling passage toward an opposing surface of the internal cooling passage and terminates prior to contacting the opposing surface of the internal cooling passage, and each of the opposing set of s-shaped trip strips further comprising a first linear trip strip formed on the respective surface of the internal cooling passage proximate an s-shaped trip strip, wherein the first linear trip strip extends in an aft direction from an area defined between the first middle segment and the second middle segment and proximate one of the peak or the trough.

16. The internally cooled airfoil of claim 15 , further comprising a second linear trip strip formed on the respective surface of the internal cooling passage and extending away from the s-shaped trip strip and the first linear trip strip.

17. The internally cooled component of claim 15 , wherein the s-shaped trip strip is off-center relative to the respective surface of the internal cooling passage.

Assignees

• United Technologies Corp

Inventors

• King Christopher
• Pietraszkiewicz Edward F

Classifications

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F05D2240/81

  Cooled platforms · CPC title

• F02C7/18

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

• F05D2240/35

  Combustors or associated equipment · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title