Forward compartment baffle arrangement for a geared turbofan engine
A baffle within a gas turbine engine includes a cylindrical flange with a multiple of holes at least partially therearound.
1. An engine case assembly within a gas turbine engine comprising:
a baffle located radially inboard of an annular core flow path of the gas turbine engine, said baffle defined around an engine central longitudinal axis, wherein said baffle defines an axial length approximately 70%+25%/−30% of an axial length of said front center body from a forward most inner diameter bolt flange to an aft most inner diameter bolt flange, said baffle having a cylindrical flange with a multiple of holes at least partially therearound.
2. The assembly as recited in claim 1 , wherein said baffle projects into the front center body, starting from a similar axial position at the forward most inner diameter bolt flange.
3. The assembly as recited in claim 1 , further comprising an oil recovery gutter axially offset from said multiple of holes.
4. The assembly as recited in claim 3 , wherein said oil recovery gutter is radially offset from said flange.
5. The assembly as recited in claim 1 , wherein said multiple of holes are defined in a multiple of rows.
6. The assembly as recited in claim 1 , wherein said cylindrical flange extends from a bearing support.
7. The assembly as recited in claim 1 , wherein said cylindrical flange extends from the front center body.
8. A gas turbine engine comprising:
an epicyclic gear system with a multiple of oil passages that extend through a ring gear of said epicyclic gear system;
a bearing support;
a baffle mounted to said bearing support to at least partially surround said epicyclic gear system, said baffle having an oil recovery gutter outboard of said multiple of oil passages, and a multiple of holes downstream of said oil recovery gutter, said oil recovery gutter axially aligned with said multiple of oil passages to receive oil slung therefrom.
9. The gas turbine engine as recited in claim 8 , wherein said epicyclic gear system is a planetary gear system.
10. The gas turbine engine as recited in claim 8 , wherein said epicyclic gear system is a star gear system.
11. The gas turbine engine as recited in claim 8 , wherein said bearing support is a #1/1.5 bearing support that defines a cylindrical flange that extends axially therefrom relative to an engine central longitudinal axis.
12. The gas turbine engine as recited in claim 11 , wherein said cylindrical flange extends from a front center body that defines the annular core flow path.
13. The gas turbine engine as recited in claim 8 , further comprising a knife seal engaged with said baffle.
14. The gas turbine engine as recited in claim 8 , wherein said oil recovery gutter is manufactured of a softer material than said knife seal.
15. The gas turbine engine as recited in claim 8 , further comprising a bypass channel defined by said baffle.
16. The gas turbine engine as recited in claim 8 , wherein said baffle defines an axial length approximately 70%+25%/−30% of an axial length of a front center body.
17. The assembly as recited in claim 8 , wherein said oil is radially expelled through a ring gear of the epicyclic gear system through the multiple of oil passages toward the baffle.
18. An engine case assembly a gas turbine engine comprising:
a front center body that at least partially defines an annular core flow path; and
a baffle that extends from said front center body forward with respect to the core airflow through the annular core flow path into a low pressure compressor, said baffle extends toward a separate oil recover gutter.
19. The assembly as recited in claim 18 , wherein said baffle is integral with said front center body.
20. The assembly as recited in claim 18 , wherein said baffle extends toward a an oil recover gutter.
21. The assembly as recited in claim 20 , wherein said baffle includes a cylindrical flange with multiple of holes at least partially therearound.
22. The assembly as recited in claim 21 , wherein said baffle is separate from said oil recover gutter.
23. The assembly as recited in claim 18 , further comprising an oil recovery gutter axially offset from said multiple of holes.
24. The assembly as recited in claim 18 , further comprising an epicyclic gear system with a multiple of oil passages that extend through a ring gear of said epicyclic gear system, said multiple of holes are axially offset from said multiple of oil passages.