Turbomachinery airfoil with optimized heat transfer

• US 5,931,638 A
• Filed: 08/07/1997
• Issued: 08/03/1999
• Est. Priority Date: 08/07/1997
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Krause, David A., Mongillo, Dominic J. Jr., Zelesky, Mark F., Soechting, Friedrich O.
• Primary Examiner(s): Lopez, F. Daniel
• Assistant Examiner(s): WOO, RICHARD SUKYOON
• Application Number:
  US08/908,403
• Time in Patent Office: 726 Days
• Field of Search: 415/115, 415/116, 416/96 R, 416/96 A, 416/97 R, 416/97 A
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F05D 2260/204 by the use of microcircuits

Abstract

A blade or vane for a gas turbine engine includes a primary cooling system (42) with a series of medial passages (44, 46a, 46b, 46c, 48) and an auxiliary cooling system (92) with a series of cooling conduits (94). The conduits of the auxiliary cooling system are parallel to and radially coextensive with the medial passages and are disposed in the peripheral wall (16) of the airfoil between the medial passages and the airfoil external surface (28). The conduits are chordwisely situated in a zone of high heat load (104, 106) so that their effectiveness is optimized. The conduits may also be chordwisely coextensive with some of the medial passages so that coolant in the medial passages is protected from excessive temperature rise. The chordwise dimension C of the conduits is limited so that potentially damaging temperature gradients do not develop in the airfoil wall (16).

Claims

1. A coolable airfoil, comprising:

a peripheral wall having an external surface comprised of a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from an airfoil root to an airfoil tip;

a primary cooling system comprised of at least one radially extending medial passage bounded at least in part by the peripheral wall; and

an auxiliary cooling system comprised of at least one cooling conduit substantially parallel to and radially coextensive with the medial passage, the conduit disposed in the wall between the medial passage and the external surface and chordwisely situated exclusively within a zone of high heat load, the high heat load zone being from about 0% to 20% of the chordwise distance from the leading edge to the trailing edge along the suction surface and about 10% to 75% of the chordwise distance from the leading edge to the trailing edge along the pressure surface, the airfoil wall chordwisely outside the high heat load zone being devoid of the cooling conduits.

4. The coolable airfoil of claim 1, wherein the primary cooling system comprises an array of chordwisely adjacent radially extending medial passages, at least two of the medial passages being interconnected to form a cooling serpentine, the conduits being chordwisely coextensive with at least one of the interconnected medial passages.

5. The coolable airfoil of claim 1, wherein the conduits have a chordwise dimension and a lateral dimension, the chordwise dimension being no more than about three times the distance from the conduit to the external surface.

6. The coolable airfoil of claim 1, wherein the primary cooling system comprises an array of chordwisely adjacent radially extending medial passages, at least two of the medial passages being interconnected to form a cooling serpentine, the conduits being chordwisely coextensive with at least one of the interconnected medial passages, and wherein the conduit has a chordwise dimension and a lateral dimension, the chordwise dimension of each conduit being no more than about three times the distance from the conduit to the external surface.

8. The coolable airfoil of claim 1, wherein the cooling conduits are chordwisely distributed over substantially the entire high heat load zone.

9. The coolable airfoil of claim 1, wherein the cooling conduits are chordwisely distributed over substantially the entire high heat load zone along the pressure surface of the airfoil.

10. The coolable airfoil of claim 1 wherein the cooling conduits are chordwisely distributed over substantially the entire high heat load zone along the suction surface of the airfoil.

11. The coolable airfoil of claim 1, 2 or 3 wherein chordwisely adjacent cooling conduits are separated by a radially extending rib interrupted by at least one interstice.

12. The coolable airfoil of claim 11 comprising one or more radially distributed replenishment passageways extending from a medial passage to the auxiliary cooling system, the passageways being aligned with the interstices.

13. The coolable airfoil of claim 1, 2 or 3 wherein each conduit has a lateral dimension and a chordwise dimension that exceeds the lateral dimension.

14. The coolable airfoil of claim 1, 2 or 3 wherein the conduits each have a lateral dimension and a chordwise dimension and are each bounded by a perimeter surface, a portion of the perimeter surface being proximate the external surface, the proximate portion having an array of trip strips extending laterally therefrom, the trip strips having a height that exceeds about 20% of the conduit lateral dimension.

15. The coolable airfoil of claim 14 wherein the trip strips are spaced apart by a radial separation and the ratio of the radial separation to the trip strip height is between about five and ten.

16. The coolable airfoil of claim 14 wherein the trip strips have a height of about 50% of the lateral dimension.

17. The coolable airfoil of claim 15 wherein the ratio of the radial separation to the trip strip height is between about five and seven.

2. A coolable airfoil, comprising:

a peripheral wall having an external surface comprised of a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from an airfoil root to an airfoil tip;

a primary cooling system comprised of chordwisely adjacent radially extending medial passages, at least two of the medial passages being interconnected to form a cooling serpentine; and

an auxiliary cooling system comprised of at least one cooling conduit substantially parallel to and radially coextensive with the medial passages, the conduit disposed in the wall between the medial passages and the external surface, the conduit being chordwisely coextensive with at least one of the interconnected medial passages so that coolant flowing through the conduit absorbs heat from the peripheral wall thereby thermally insulating coolant flowing through the at least one medial passage.

7. The coolable airfoil of claim 2, wherein the conduit has a chordwise dimension and a lateral dimension, the chordwise dimension being no more than about three times the distance from the conduit to the external surface.

3. A coolable airfoil, comprising:

a peripheral wall having an external surface comprised of a suction surface and a pressure surface laterally spaced from the suction surface, the surfaces extending chordwisely from a leading edge to a trailing edge and radially from an airfoil root to an airfoil tip;

a primary cooling system comprised of at least one radially extending medial passage bounded at least in part by the peripheral wall; and

an auxiliary cooling system comprised of at least one cooling conduit substantially parallel to and radially coextensive with the medial passage, the conduit disposed in the wall between the medial passage and the external surface, the conduit having a chordwise dimension and a lateral dimension, the chordwise dimension being no more than about three times the distance from the conduit to the external surface.