Flow splitting first vane support for gas turbine engine
A gas turbine engine includes an engine static structure that has a fluid port. A turbine vane is supported relative to the engine static structure and includes a cooling passage. A flow splitter is provided between the engine static structure and the turbine vane. The flow splitter is configured to divide a flow upstream from the flow splitter into a first fluid flow provided to the fluid port and a second fluid flow provided to the cooling passage.
1. A gas turbine engine comprising:
an engine static structure having a fluid port;
a turbine vane supported relative to the engine static structure and including a cooling passage;
a flow splitter provided between the engine static structure and the turbine vane, the flow splitter configured to divide a flow upstream from the flow splitter into a first fluid flow provided to the fluid port and a second fluid flow provided to the cooling passage; and
a locating feature between the flow splitter and the engine static structure configured to circumferentially affix the flow splitter to the engine static structure, wherein the engine static structure includes one of a fork and a tab, and the flow splitter includes the other of the fork and the tab, the tab received in the fork and comprising the locating feature.
2. The gas turbine engine according to claim 1 , wherein the engine static structure supports a diffuser case arranged about a combustor housing to provide a diffuser plenum, an upstream flow corresponding to a diffuser flow in the diffuser plenum.
3. The gas turbine engine according to claim 1 , comprising a component in fluid communication with the fluid port, the component configured to receive the first fluid flow.
4. The gas turbine engine according to claim 1 , wherein the flow splitter is provided by an annular ring arranged radially between the engine static structure and the turbine vane to provide first and second radially spaced cavities.
5. The gas turbine engine according to claim 4 , wherein the annular ring includes an aft wall that seals against an aft platform flange of the turbine vane.
6. The gas turbine engine according to claim 4 , wherein engine static structure includes a diffuser case and a turbine case secured to one another, and the annular ring includes an aft wall captured between the diffuser case and the turbine case.
7. The gas turbine engine according to claim 1 , comprising a turbine section including a first stage array of turbine stator vanes which include the turbine vane.
8. The gas turbine engine according to claim 7 , comprising a diffuser case and a combustor case affixed relative to the engine static structure and arranged upstream from the turbine vane.
9. The gas turbine engine according to claim 7 , comprising a tangential on-board injector secured to the turbine vane and configured to provide a TOBI flow to a turbine rotor arranged downstream from the turbine vane.
10. A gas turbine engine comprising:
an engine static structure having a fluid port;
a turbine vane supported relative to the engine static structure and including a cooling passage;
a flow splitter provided between the engine static structure and the turbine vane, the flow splitter configured to divide a flow upstream from the flow splitter into a first fluid flow provided to the fluid port and a second fluid flow provided to the cooling passage; and
a locating feature between the flow splitter and the turbine vane configured to circumferentially affix the turbine vane to the flow splitter, wherein the flow splitter includes one of a fork and a tab, and the turbine vane includes the other of the fork and the tab, the tab received in the fork and comprising the locating feature.
11. The gas turbine engine according to claim 10 , comprising a ring seal engaging the other of the fork and the tab of the turbine vane.
12. A method of flowing fluid through a gas turbine engine, comprising:
providing a diffuser flow; and
splitting the diffuser flow into first and second fluid flows, wherein the second fluid flow is provided to a turbine vane airfoil, wherein the first fluid flow is provided to a component through a bleed port in an engine static structure, the splitting step performed by providing a flow splitter arranged radially between the engine static structure and the turbine vane, wherein the flow splitter includes an annular ring having an axially extending wall providing inner and outer diameters, the axially extending wall protruding from an intermediate portion of a radially extending wall, and one of a tab and a fork extending radially outward from the outer diameter, and another of a tab and a fork extending radially inward from the inner diameter.