Internally cooled airfoil

Patent metadata

Field	Value
Publication number	US-9810071-B2
Application number	US-201314039181-A
Country	US
Kind code	B2
Filing date	Sep 27, 2013
Priority date	Sep 27, 2013
Publication date	Nov 7, 2017
Grant date	Nov 7, 2017

Abstract

An internally cooled airfoil for a gas turbine engine has a hollow airfoil body defining a core cavity. An insert is mounted in the core cavity. A cooling gap is provided between the insert and the hollow airfoil body. A plurality of standoffs project across the cooling gap. Trip-strips projecting laterally between adjacent standoffs. The trip-strips and the standoffs may be integrated into a unitary heat transfer feature.

First claim

What is claimed is:

1. An internally cooled airfoil for a gas turbine engine, comprising a hollow airfoil body including a pressure sidewall and a suction sidewall extending chordwise from a leading edge to a trailing edge, the pressure and suction sidewalls having an internal surface bounding a core cavity, an insert mounted in the core cavity in spaced-apart relationship with said internal surface to define a cooling gap therewith, and a plurality of standoffs projecting from said internal surface of said pressure and suction sidewalls into the cooling gap toward the insert, a plurality of trip-strips projecting from said internal surface of the pressure and suction sidewalls, the trip-strips being intersperse between adjacent standoffs and extending laterally with respect thereto, wherein the plurality of standoffs include standoffs in a mid-chord area of the pressure and suction sidewalls, the trip-strips intersecting the standoffs in the mid-chord area.

2. The internally cooled airfoil defined in claim 1 , wherein at least one of the standoffs has a trip-strip integrated thereto as a lateral extension at a base of the at least one of the standoffs.

3. The internally cooled airfoil defined in claim 2 , wherein each of said at least one of the standoffs has at least one trip-strip portion extending laterally from a side thereof, the at least one trip-strip portion being oriented transversally to a flow direction of coolant through the cooling gap.

4. The internally cooled airfoil defined in claim 3 , wherein the at least one of the standoffs consist of cylindrical projections extending from the internal surface of the pressure and suction sidewalls, and wherein the at least one trip-strip portion is provided in the form of a wing-like projection extending from a base portion of a corresponding one of the cylindrical projections on said internal surface of the pressure and suction sidewalls.

5. The internally cooled airfoil defined in claim 1 , wherein each of the plurality of standoffs have opposed upstream and downstream sides relative to a flow direction of coolant through the cooling gap, said opposed upstream and downstream sides being spaced by lateral sides, and wherein each of the plurality of trip-strips project from at least one of said lateral sides.

6. The internally cooled airfoil defined in claim 1 , wherein the hollow airfoil body has a thickness inspection region on at least one of the pressure and the suction sidewall thereof, wherein said thickness inspection region corresponds to a standoff free region on said internal surface, and wherein the standoffs located immediately upstream of the standoff free region relative to a flow direction of coolant are provided with opposed facing trip-strip portions.

7. The internally cooled airfoil defined in claim 6 , wherein the standoffs immediately adjacent to the standoff free region and disposed between upstream and downstream ends of the standoff free region relative to the flow direction of coolant are provided with trip-strip portions extending towards the standoff free region.

8. The internally cooled airfoil defined in claim 2 , wherein said at least one of said standoffs has first and second trip-strip portions extending from opposed lateral sides thereof, said first trip-strip portion being shorter than said second trip-strip portion.

9. The internally cooled airfoil defined in claim 1 , wherein the airfoil body is an airfoil casting and the insert is a sheet metal insert, and wherein the standoffs and the trip-strips integrally extend from the inner surface of the airfoil casting.

10. The internally cooled airfoil defined in claim 1 , wherein the internally cooled airfoil is a turbine vane.

11. An internally cooled turbine vane comprising a hollow airfoil body defining a core cavity, an insert mounted in the core cavity, a cooling gap between the insert and pressure and suction sidewalls of the hollow airfoil body, a plurality of standoffs projecting across the cooling gap, and trip-strips projecting laterally between adjacent standoffs and only partway through the cooling gap between the insert and the pressure and suction sidewalls of the hollow airfoil body, the plurality of standoffs being distributed over an internal surface of the pressure and suction sidewalls, and including standoffs in a mid-chord area of the pressure and the suction sidewalls, the trip-strips intersecting the standoffs in the mid-chord area.

12. The internally cooled turbine vane defined in claim 11 , wherein the standoffs have at least one trip-strip extending laterally from a side thereof, the at least one trip-strip being oriented transversally to a flow direction of coolant through the cooling gap.

13. The internally cooled turbine vane defined in claim 11 , wherein the standoffs consist of cylindrical projections extending from the internal surface of the pressure and suction sidewalls, and wherein the trip-strips are provided in the form of wing-like projections extending from a base portion of the cylindrical projections.

14. The internally cooled turbine vane defined in claim 11 , wherein each of the plurality of standoffs have opposed upstream and downstream sides relative to a flow direction of coolant through the cooling gap, said opposed upstream and downstream sides being spaced by lateral sides, and wherein each of the plurality of trip-strips project from each of the at least one of said lateral sides.

15. The internally cooled turbine vane defined in claim 11 , wherein the hollow airfoil body has a thickness inspection region on at least one of the pressure and the suction sidewall thereof, wherein said thickness inspection region corresponds to a standoff free region on an inwardly facing surface of said at least one of the pressure and suction sidewalls, and wherein the standoffs located immediately upstream of the standoff free region relative to a flow direction of coolant are provided with opposed facing trip-strips.

16. The internally cooled turbine vane defined in claim 15 , wherein the standoffs immediately adjacent to the standoff free region and disposed between upstream and downstream ends of the standoff free region relative to the flow direction of coolant are provided with trip-strips extending towards the standoff free region.

17. The internally cooled turbine vane defined in claim 11 , wherein at least one of said standoffs has first and second trip-strips extending from opposed lateral sides thereof, said first trip-strip being shorter than said second trip-strip.

18. The internally cooled turbine vane defined in claim 11 , wherein the airfoil body is an airfoil casting and the insert is a sheet metal insert, and wherein the standoffs and the trip-strips integrally extend from the inner surface of the airfoil casting.

Assignees

• Pratt & Whitney Canada

Inventors

• Papple Michael

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

• F05D2260/22141

  using fins or ribs · CPC title

• F01D5/18 Primary

  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

• F05D2250/241

  spherical · CPC title

• F05D2260/2212

  by creating turbulence · CPC title