Metering hole geometry for cooling holes in gas turbine engine
A turbine may include a blade coupled to a rotor, a vane upstream from the blade and coupled to a vane support that defines a metering hole, and a blade outer air seal disposed radially outward from the blade and downstream from the vane support. An impingement surface may be disposed between the vane support and the blade outer air seal. The impingement surface may be oriented at an angle to the metering hole of between 50 degrees and 5 degrees.
1. A metering assembly in a turbine section of a gas turbine engine, the metering assembly comprising:
a vane;
a vane support radially outward of the vane and configured to secure the vane to a case;
a wall of the vane support defining a metering hole configured to eject a jet of coolant, wherein the metering hole is configured to eject the jet of coolant at a first angle normal to a downstream surface of the wall;
an impingement structure disposed downstream from the wall and configured to obstruct the jet of coolant from the metering hole, wherein the impingement structure is an extension of the vane support, and wherein the impingement structure is configured such that the jet of coolant contacts an impingement surface of the impingement structure at a second angle between 45 degrees and 10 degrees relative to the impingement surface; and
a blade outer air seal disposed downstream from the vane support, wherein the impingement surface of the impingement structure is forward of a forwardmost end of the blade outer air seal.
2. The metering assembly of claim 1 , wherein the second angle is between 35 degrees and 10 degrees relative to the impingement surface.
3. The metering assembly of claim 1 , wherein the metering hole has an aspect ratio of at least 2:1, wherein the aspect ratio is a ratio of a length of the metering hole to a diameter of the metering hole.
4. A turbine, comprising: a blade coupled to a rotor; a vane upstream from the blade; a vane support coupled to the vane, wherein the vane support defines a metering hole configured to eject a jet of coolant at a first angle normal to a downstream surface of the vane support; a blade outer air seal disposed radially outward from the blade and downstream from the vane support; a case coupled to the vane support and the blade outer air seal; and an impingement surface disposed downstream of the metering hole, wherein the impingement surface is formed by the case, and wherein the impingement surface is oriented such that the jet of coolant contacts the impingement surface at a second angle of between 50 degrees and 5 degrees relative to the impingement surface, and wherein the impingement surface is forward of a forward most end of the blade outer air seal.
5. The turbine of claim 4 , wherein the second angle is between 45 degrees and 10 degrees.
6. The turbine of claim 4 , wherein the second angle is between 35 degrees and 15 degrees.
7. The turbine of claim 4 , wherein the metering hole has an aspect ratio of at least 2:1, wherein the aspect ratio is a ratio of a length of the metering hole to a diameter of the metering hole.
8. A gas turbine engine comprising:
a compressor section configured to compress a gas, wherein a coolant is bled from the compressor section;
a combustor downstream from the compressor section;
a turbine section downstream from the combustor, the turbine section comprising:
a vane support defining a metering hole configured to eject a jet of the coolant at a first angle normal to a downstream surface of the vane support;
an impingement surface disposed downstream from the metering hole, wherein the impingement surface is formed by at least one of an extension of the vane support or a case in the turbine section, and wherein the impingement surface is configured such that the jet of the coolant contacts the impingement surface at a second angle of between 50 degrees and 5 degrees relative to the impingement surface; and
a blade outer air seal downstream from the vane support, and wherein the impingement surface is forward of a forwardmost end of the blade outer air seal.
9. The gas turbine engine of claim 8 , wherein the second angle is between 45 degrees and 10 degrees.
10. The gas turbine engine of claim 8 , wherein the metering hole has an aspect ratio of at least 2:1, wherein the aspect ratio is a ratio of a length of the metering hole to a diameter of the metering hole.