Sequential cooling insert for turbine stator vane

Patent metadata

Field	Value
Publication number	US-9611745-B1
Application number	US-201414511211-A
Country	US
Kind code	B1
Filing date	Oct 10, 2014
Priority date	Nov 13, 2012
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

A sequential flow cooling insert for a turbine stator vane of a small gas turbine engine, where the impingement cooling insert is formed as a single piece from a metal additive manufacturing process such as 3D metal printing, and where the insert includes a plurality of rows of radial extending impingement cooling air holes alternating with rows of radial extending return air holes on a pressure side wall, and where the insert includes a plurality of rows of chordwise extending second impingement cooling air holes on a suction side wall. The insert includes alternating rows of radial extending cooling air supply channels and return air channels that form a series of impingement cooling on the pressure side followed by the suction side of the insert.

First claim

I claim the following:

1. An impingement cooling insert for a turbine stator vane of a gas turbine engine, the impingement cooling insert comprising:
a pressure side wall;
a suction side wall;
an inlet cover plate with a plurality of cooling air supply openings;
the pressure side wall having a plurality of spanwise extending impingement cooling air holes channels;
the suction side wall having a plurality of chordwise extending impingement cooling air channels;
a plurality of radial extending cooling air supply channels alternating with a plurality of radial extending cooling air return channel;
the pressure side wall having a row of first impingement cooling air holes connected to each of the radial extending cooling air supply channels;
the pressure side wall having a row of return air holes connected to each of the plurality of cooling air return channels;
the suction side wall having a row of second impingement cooling air holes connected to each of the cooling air return channels; and,
the impingement cooling insert is formed as a single piece.

2. The impingement cooling insert of claim 1 , and further comprising:
the impingement cooling insert includes at least two radial extending seal grooves each extending a spanwise length of the insert.

3. The impingement cooling insert of claim 1 , and further comprising:
the impingement cooling insert has a radial height of less than one inch.

4. The impingement cooling insert of claim 1 , and further comprising:
the impingement cooling insert has a radial height of around ⅝ th of an inch.

5. The impingement cooling insert of claim 1 , and further comprising:
the first rows of impingement cooling air holes is of a smaller diameter than the return air holes.

6. The impingement cooling insert of claim 1 , and further comprising:
a bottom cap to enclose the cooling air supply channels and the return air channels; and,
the bottom cap having a slot to position the impingement cooling insert within an airfoil.

7. An impingement cooling insert for a turbine stator vane of a gas turbine engine, the impingement cooling insert comprising:
a pressure side wall;
a suction side wall;
an inlet cover plate with a plurality of cooling air supply openings;
a plurality of radial extending cooling air supply channels alternating with a plurality of radial extending cooling air return channels formed between the pressure side wall and the suction side wall of the insert;
the plurality of radial extending cooling air supply channels connected to the plurality of cooling air supply openings;
the pressure side wall having a row of first impingement cooling air holes connected to each of the radial extending cooling air supply channels;
the pressure side wall having a row of return air holes connected to each of the radial extending cooling air return channels;
the suction side wall having a row of second impingement cooling air holes connected to each of the cooling air return channels; and,
the impingement cooling insert is formed as a single piece.

8. The impingement cooling insert of claim 7 , and further comprising:
the impingement cooling insert includes at least two radial extending seal grooves each extending a spanwise length of the insert.

9. The impingement cooling insert of claim 7 , and further comprising:
the impingement cooling insert has a radial height of less than one inch.

10. The impingement cooling insert of claim 7 , and further comprising:
the impingement cooling insert has a radial height of around ⅝ th of an inch.

11. The impingement cooling insert of claim 7 , and further comprising:
a bottom cap to enclose the cooling air supply channels and the return air channels; and,
the bottom cap having a slot to position the impingement cooling insert within an airfoil.

Assignees

• Jones Russel B
• Florida Turbine Tech Inc

Inventors

• Jones Russel B

Classifications

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F01D5/188 Primary

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F05D2250/191

  perforated · CPC title

• F01D9/065

  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