Sequential cooling insert for turbine stator vane
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.
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.