Necked debris separator for a gas turbine engine
A debris separator for a gas turbine engine component includes a first body section along an axis, the first body section comprising a first orifice, a neck section adjacent to the first body section along the axis, and a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.
1. A debris separator for a gas turbine engine component, comprising:
a first body section along an axis, wherein the first body section comprises atleast one inlet orifice further comprising a slot, the first body section comprising a first orifice;
a neck section adjacent to the first body section along the axis; and
a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.
2. The debris separator as recited in claim 1 , wherein the first body section has a closed end and said first orifice opens radially outwardly.
3. The debris separator as recited in claim 1 , wherein the second body section is of a diameter less than a diameter of the first body section.
4. The debris separator as recited in claim 1 , wherein the second body section is flared.
5. The debris separator as recited in claim 1 , wherein the first body section and the second body section are tubular.
6. A gas turbine engine, comprising:
a vane support with a vane support aperture; and
a debris separator according to claim 1 mounted at least partially through the aperture in the vane support.
7. The gas turbine engine as recited in claim 6 , wherein the debris separator comprises:
a first body section along an axis, the first body section comprising a first orifice;
a neck section adjacent to the first body section along the axis; and
a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.
8. The gas turbine engine as recited in claim 7 , wherein the neck section abuts the vane support and the second body region passes at least partially through the vane support aperture.
9. The gas turbine engine as recited in claim 8 , wherein the second body section is flared to retain the debris separator within the vane support aperture.
10. The gas turbine engine as recited in claim 7 , wherein the debris separator comprises:
a first body section along an axis, the first body section defining the first orifice transverse to the vane support aperture.
11. The gas turbine engine as recited in claim 7 , wherein the debris separator comprises: a neck section adjacent to the first body section along the axis, the neck section abuts the vane support aperture.
12. The gas turbine engine as recited in claim 7 , wherein the debris separator comprises: a second body section along the axis adjacent to a neck region, the second body section passes at least partially through the vane support aperture.
13. The gas turbine engine as recited in claim 7 , wherein the vane support aperture defines an axis parallel to an engine axis.
14. A method of installing a debris separator according to claim 1 for a gas turbine engine component, the method comprising:
inserting a debris separator into a vane support aperture; and
flaring the debris separator opposite a closed end to retain the debris separator in the vane support aperture.
15. The method as recited in claim 14 , wherein inserting the debris separator into the vane support aperture comprises inserting the debris separator such that a neck section contacts upon the vane support.
16. The method as recited in claim 15 , wherein flaring the debris separator comprises flaring a second body section downstream of the neck section.
17. The method as recited in claim 15 , further comprising integrally forming the debris separator as an integral tubular component.
18. The method as recited in claim 15 , further comprising integrally forming a closed end, a first body section, a second body section, and the neck section between the first and second body section.