×

Impingement cooling of turbine blades or vanes

  • US 9,863,255 B2
  • Filed: 11/22/2012
  • Issued: 01/09/2018
  • Est. Priority Date: 02/15/2012
  • Status: Active Grant
First Claim
Patent Images

1. A turbine assembly comprising:

  • a basically hollow aerofoil and at least one impingement device,wherein the hollow aerofoil comprises at least one first side wall extending from a leading edge towards a trailing edge of the hollow aerofoil, and at least one cavity in which in an assembled state of the at least one impingement device in the hollow aerofoil the at least one impingement device is arranged;

    at a predetermined distance from an inner surface of the at least one cavity for impingement cooling of the inner surface; and

    to form a flow channel for a cooling medium extending from the leading edge towards the trailing edge, andwherein the at least one impingement device comprises a first piece and a second piece arranged side by side in an axial direction from the leading edge to the trailing edge, with the first piece located towards the leading edge and the second piece located towards the trailing edge, and with an axial distance therebetween that forms a first flow passage that provides a passage from one side of the hollow aerofoil towards an opposite side of the hollow aerofoil, andat least one first blocking element arranged in the flow channel between a side of the second piece that is closer to the leading edge than to the trailing edge and the at least one first side wall of the hollow aerofoil, wherein the at least one first side wall comprises a suction side wall of the hollow aerofoil, and wherein the at least one first blocking element is configured to block a flow of cooling medium in a direction from the leading edge to the trailing edge of the hollow aerofoil, thereby denying the flow of cooling medium direct access to a section of the flow channel downstream of the at least one first blocking element while directing the flow of cooling medium into the first flow passage away from the suction side wall towards a pressure side wall of the hollow aerofoil, wherein the flow of cooling medium then flows directly from the first flow passage axially toward the trailing edge between the second piece and the pressure side wall.

View all claims
  • 2 Assignments
Timeline View
Assignment View
    ×
    ×