Gas turbine vane

• US 4,697,985 A
• Filed: 03/06/1985
• Issued: 10/06/1987
• Est. Priority Date: 03/13/1984
• Status: Expired due to Term

• Current Assignee: Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Original Assignee: Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Inventors: Suzuki, Isamu
• Primary Examiner(s): Garrett, Robert E.
• Assistant Examiner(s): Kwon, John
• Application Number:
  US06/708,801
• Time in Patent Office: 944 Days
• Field of Search: 415/115, 416/95, 416/96 R, 416/96 A, 416/97 R
• 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 gas turbine vane generally comprises an outer hollow vane member provided with a plurality of ribs aligned on the inner wall of the outer vane member and an insertion member of vane shape inserted into the outer hollow vane member so as to rigidly engage with the ribs. A turbulence chamber is defined between the leading edge portions of the outer and inner vane members, and the inner hollow insertion member is provided with numerous orifices at its leading edge portion for injecting cooling fluid into this turbulence chamber. A plurality of cooling passages operatively connected to the turbulence chamber are formed between the flank walls of the outer and inner vane members, and a plurality of orifices are further provided through the flank walls of the inner insertion member so as to communicate the interior thereof with the cooling passages.

Claims

1. A gas turbine vane comprising:

an outer vane member of hollow vane shape having flank walls, an exterior surface and an inner wall surface, the inner wall surface having a plurality of spaced-apart projections thereon extending in a vane chordwise direction;

an insertion member of hollow shape having flank wall parts and being inserted into said outer vane member and tightly engaged with said projections;

a turbulence chamber formed between said outer vane member at a leading edge part thereof and said insertion member;

means for carrying cooling fluid from said turbulence chamber to a plurality of rear exhaust ports, said carrying means comprising a plurality of cooling passages which are laterally distinct from one another formed between said outer vane member, said insertion member, and said projections;

first fluid injection means for injecting fluid into said turbulence chamber;

second fluid injection means positioned intermediate between said turbulence chamber at the flank wall parts of said insertion member and said exhaust ports for feeding injecting fluid into each of said cooling passages to further cool a trailing edge portion of said outer vane member;

flow restricting means disposed in each of said cooling passages to control the length of time spent by said fluid in said turbulence chamber and to control the pressure of said fluid in said turbulence chamber; and

means for film cooling the exterior surface of said outer vane member, said film cooling means including a plurality of slots positioned at the flank wall of said outer vane member and means for allowing one-way flow of fluid between said cooling passages and the exterior surface of said outer vane member.

2. A gas turbine vane according to claim 1, wherein said one-way flow allowing means comprises said cooling passages and said flow restricting means.

3. The gas turbine vane according to claim 1 in which the second injection means are adapted to inject the cooling fluid against the inner surface of the flank walls of the outer vane member.

4. The gas turbine vane according to claim 1 wherein said flow rate regulating means comprises a throttling member for reducing the cross-sectional area of said cooling passage.

5. The gas turbine vane according to claim 4 wherein said throttling member is constituted by a throttling orifice.

6. The gas turbine vane according to claim 1 wherein said tiered slots are formed at positions of the flank wall of said outer vane member in front of said fluid flow rate regulating means.

7. The gas turbine vane according to claim 1 wherein said projections are provided only on the inner flank walls of said outer vane member.

8. The gas turbine vane according to claim 1 wherein a plurality of fin members are further provided for portions near the trailing edge portions of said outer vane member.

9. The gas turbine vane according to claim 1, wherein said projections are provided on both the inner wall of the leading edge portion and the inner flank walls of said outer vane member.

10. The gas turbine vane according to claim 1, wherein said flow rate regulating means is positioned between said first and said second invention means.