Cooled turbine vane

• US 4,297,077 A
• Filed: 07/09/1979
• Issued: 10/27/1981
• Est. Priority Date: 07/09/1979
• Status: Expired due to Term

• Current Assignee: Siemens Westinghouse Power Corporation
• Original Assignee: Westinghouse Electric Corporation (Paramount Global (f/k/a ViacomCBS Inc.))
• Inventors: Durgin, George A., Demers, Daniel E.
• Primary Examiner(s): Smith, Leonard E.
• Application Number:
  US06/055,833
• Time in Patent Office: 841 Days
• Field of Search: 416/96 R, 416/96 A, 416/97 R, 416/97 A, 415/115
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F05D 2260/201 by impingement of a fluid

Abstract

A hollow gas turbine vane is shown enclosing, in spaced relation, a vane insert for receiving cooling air. The insert has a plurality of apertures for selectively directing jets of the cooling air against the internal walls of the vane. A portion of the air is discharged from within the vane chamber through a slit in the trailing edge which contains cooling pins extending transversely thereacross to maintain the slit dimensionally stable and also induce turbulence in the exhausting cooling air to improve its cooling effectiveness. Certain apertures in the insert adjacent the trailing edge are selectively directed to cause jets of the cooling air to impinge at the base of certain of the pins in the inlet area of the slit to promote turbulence in the air entering the slit and adjacent the internal face, thereby maximizing heat transfer from the slit walls to the air.

Claims

1. A turbine vane having an airfoil portion providing a leading edge, a suction side, a pressure side and a trailing edge, and wherein said airfoil portion is generally hollow to define an internal chamber to receive cooling air, a slit from said internal chamber through said trailing edge generally throughout the radial extent of said airfoil portions, and wherein the opposed internal walls defining said slit converge from generally a broad inlet area adjacent said chamber to a relatively narrow passage downstream thereof, a plurality of radial rows of pin-like members extending transversely across said slit and integral with the opposed walls defining said slit, and wherein the members of each row are radially offset with respect to the members of any adjacent row to intercept the cooling air flowing through said slit at different levels, a hollow insert disposed within said chamber for initially receiving at least a portion of the cooling air entering said chamber, said insert having a wall member generally adjacent said slit inlet area and apertures in said insert wall for directing cooling air exiting therethrough primarily in a direction to impinge on a selected plurality of junctures of said members and at least one wall of said slit to provide sufficient velocity in said cooling air to cause said juncture to induce turbulence in said cooling air as it flows adjacent said wall and downstream of said juncture to effectively cool said vane.

2. Turbine vane structure according to claim 1 wherein said inlet area includes at least a first and second row of members extending transversely thereacross, and wherein said apertures in said insert are aimed to direct relatively high velocity cooling air at the juncture of said members in said first and second row adjacent one wall of said slit.

3. Turbine vane structure according to claim 2 having a row of apertures from said chamber through said pressure side of said airfoil generally upstream from said trailing edge to deliver a film of cooling air to the downstream surface of said vane and wherein said insert apertures are aimed at the juncture of said members and sais slit wall corresponding to the suction side of said airfoil.

4. Turbine vane structure according to claim 2 wherein said slit walls converge downstream of said second row of members to a narrow width wherein the velocity of air passing therethrough is thereafter sufficient for said downstream members to induce turbulent flow adjacent said slit walls.

5. A generally hollow turbine vane defining a chamber in the airfoil portion thereof for receiving pressurized cooling air, said airfoil portion defining a leading edge and a downstream trailing portion terminating in a trailing edge, a coolling air outlet slit from said chamber through said trailing edge, with said slit defined by opposed internal walls converging from a relatively broad inlet area to a relatively narrow air passage at a downstream intermediate point, a plurality of rows of radially staggered projections integral with said opposed internal walls extending across said slit, with at least one row in said inlet area, and a generally hollow insert in said chamber for receiving at least a portion of the pressurized air, said insert having a wall member generally adjacent said one row of projections and cooling fluid passages in said wall for directing discrete air flow in a direction to impinge on the juncture of said one row and the slit wall whereby said juncture induces turbulence in said cooling air as it flows downstream thereof to cooling the trailing portion of said vane.

6. Structure according to claim 5 including a plurality of radial rows of projections in said inlet area and said insert includes cooling fluid passages for directing cooling air flow to the juncture of said projections in said plurality of rows with at last one wall of said slit.

7. Structure according to claim 6 wherein said internal wall of said slit receiving said discrete cooling fluid paths as directed by said insert is the internal wall of the suction side of said vane.

8. Structure according to claim 7 wherein said slit walls converge downstream of a second radial row of said projections to a narrow width wherein the velocity of cooling air flowing over the further downstream rows of projection is sufficient for said projections to cause turbulence in said air adjacent said slit walls to cool the trailing portion of said vane.