Multiple injector holes for gas turbine engine vane
A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.
1. A vane for use in a turbine section of a gas turbine engine comprising:
an airfoil extending from a radially outer platform to a radially inner platform;
a pair of legs extending radially inwardly from said radially inner platform, and an air flow passage extending through said radially outer platform, through said airfoil, and into a chamber defined between said pair of legs, one of said pair of legs including a plurality of injector holes, configured to allow air from said radially outer platform to pass outwardly of said plurality of injector holes;
said plurality of holes includes at least a first hole positioned radially outwardly of a second hole;
said first and second holes have an elliptical shape at an outer surface of said one of said pair of legs;
wherein said one of said pair of legs extends further radially inward than does a second of said pair of legs;
said second of said pair of legs is attached to a first seal, and a second separate seal is attached to said one of said pair of legs; and
said chamber extends to an end of said vane, with said second separate seal extending from said one of said pair of legs in a direction of said second of said pair of legs, with an end of said second separate seal spaced from said second of said pair of legs such that said chamber communicates air radially inwardly through a gap between said end of said second separate seal and said second of said pair of legs.
2. The vane as set forth in claim 1 , wherein at least one of said first and second holes extends at an angle that is non-parallel to a central axis of an engine incorporating said vane.
3. A duplex vane for use in a turbine section of a gas turbine engine comprising:
a first airfoil extending from a radially outer platform to a radially inner platform;
a second airfoil extending between said radially outer platform and said radially inner platform; and
each of said first and second airfoils having a pair of legs extending radially inwardly from said radially inner platform, and an air flow passage extending through said radially outer platform, through a respective one of said first and second airfoils, and into a chamber defined between said pair of legs, one of said pair of legs including a plurality of injector holes, configured to allow air from said radially outer platform to pass outwardly of said plurality of injector holes;
said plurality of injector holes associated with each of said first and second airfoils and wherein said plurality of injector holes include a first hole and a second hole associated with each of said first and second airfoils, with said first hole positioned radially outwardly of said second hole, and each of said first and second holes associated with each of said first and second airfoils having an elliptical shape at an outer surface of said one of said pair of legs;
wherein said one of said pair of legs extends further radially inward than does a second of said pair of legs;
said second of said pair of legs is attached to a first seal, and a second separate seal is attached to said one of said pair of legs; and
said chamber extends to an end of said vane, with said second separate seal extending from said one of said pair of with legs in a direction of said second of said pair of legs, with an end of said second separate seal spaced from said second of said pair of legs such that said chamber communicates air radially inwardly through a gap between said end of said second separate seal and said second of said pair of legs.
4. The duplex vane as set forth in claim 3 , wherein at least one of said first and second holes extends at an angle that is non-parallel to a central axis of an engine incorporating said vane.