Tangential onboard injector inlet extender
A diffuser case for a gas turbine engine including: a pre-diffuser; a diffuser case defining a dump region, an inner plenum, and an outer plenum, the pre-diffuser being fluidly connected to the inner plenum and the outer plenum through the dump region; a tangential onboard injector module fluidly connected to the inner plenum through inlet orifice located in the diffuser case proximate an aft end of the inner plenum; and an inlet extender initiating at the inlet orifice of the tangential onboard injector module, extends through the inner plenum, and terminates at a distal end proximate the pre-diffuser.
1. A diffuser case for a gas turbine engine, comprising:
a pre-diffuser;
the diffuser case defining a dump region downstream of the pre-diffuser, an inner plenum, and an outer plenum, the pre-diffuser being fluidly connected to the inner plenum and the outer plenum through the dump region;
a tangential onboard injector module fluidly connected to the inner plenum through an inlet orifice located in the diffuser case proximate an aft end of the inner plenum;
an inlet extender initiating at the inlet orifice of the tangential onboard injector module, the inlet extender extending through the inner plenum, and terminates at a distal end proximate the pre-diffuser, the distal end being a free end; and
wherein the distal end of the inlet extender is located in the dump region between an aft end of the pre-diffuser and a forward end of a forward dome of a combustor of the gas turbine engine, the inlet extender fluidly separates the inner plenum into a first inner plenum and a second inner plenum, each having an inlet opening proximate to the distal end of the inlet extender and the second inner plenum being radially outward of the first inner plenum, wherein the inlet orifice is fluidly connected to the first inner plenum.
2. The diffuser case of claim 1 , further comprising
a radially inward wall at least partially defining the inner plenum, wherein the inlet extender is located proximate the radially inward wall.
3. The diffuser case of claim 1 , wherein the pre-diffuser includes a guide wall defining the pre-diffuser, and wherein the inlet extender proximate the distal end is shaped to be perpendicular to the guide wall of the pre-diffuser.
4. The diffuser case of claim 1 , wherein the pre-diffuser includes a guide wall defining the pre-diffuser, and wherein an angle between the guide wall of the pre-diffuser and the inlet extender proximate the distal end is less than or equal to 90 degrees.
5. The diffuser case of claim 1 , wherein the pre-diffuser includes a guide wall defining the pre-diffuser, and wherein an angle between the guide wall of the pre-diffuser and the inlet extender proximate the distal end is less than 90 degrees.
6. The diffuser case of claim 1 , wherein the pre-diffuser includes a guide wall defining the pre-diffuser, and wherein an angle between the guide wall of the pre-diffuser and the inlet extender proximate the distal end is equal to 90 degrees.
7. The diffuser case of claim 1 , further comprising:
an orifice located in the inlet extender fluidly connecting the first inner plenum and the second inner plenum; and
a ramp located opposite the orifice.
8. The diffuser case of claim 7 , further comprising
a radially inward wall at least partially defining the inner plenum, wherein the inlet extender is located proximate the radially inward wall,
wherein the ramp extends away from the radially inward wall and towards the orifice.
9. The diffuser case of claim 7 , further comprising
a radially inward wall at least partially defining the inner plenum, wherein the inlet extender is located proximate the radially inward wall,
wherein the ramp is orientated at an angle relative to the radially inward wall, the angle being less than 90 degrees as measured between the radially inward wall and an aft side of the ramp.
10. A gas turbine engine, comprising:
a pre-diffuser;
a diffuser case defining a dump region downstream of the pre-diffuser, an inner plenum, and an outer plenum, the pre-diffuser being fluidly connected to the inner plenum and the outer plenum through the dump region;
a combustor housed within the diffuser case between the inner plenum and the outer plenum;
a tangential onboard injector module fluidly connected to the inner plenum through an inlet orifice located in the diffuser case proximate an aft end of the inner plenum; and
an inlet extender initiating at the inlet orifice of the tangential onboard injector module, the inlet extender extending through the inner plenum, and terminates at a distal end proximate the pre-diffuser, the distal end being a free end; and
wherein the distal end of the inlet extender is located in the dump region between an aft end of the pre-diffuser and a forward end of a forward dome of the combustor, the inlet extender fluidly separates the inner plenum into a first inner plenum and a second inner plenum, each having an inlet opening proximate to the distal end of the inlet extender and the second inner plenum being radially outward of the first inner plenum, wherein the inlet orifice is fluidly connected to the first inner plenum.
11. The gas turbine engine of claim 10 , wherein the inlet extender is interposed between the combustor and a radially inward wall of the diffuser case.
12. The gas turbine engine of claim 10 , wherein the pre-diffuser includes a guide wall defining the pre-diffuser, and wherein the inlet extender proximate the distal end is shaped to be perpendicular to the guide wall of the pre-diffuser.
13. The gas turbine engine of claim 10 , wherein the pre-diffuser includes a guide wall defining the pre-diffuser, and wherein an angle between the guide wall of the pre-diffuser and the inlet extender proximate the distal end is less than or equal to 90 degrees.
14. The gas turbine engine of claim 10 , wherein the pre-diffuser includes a guide wall defining the pre-diffuser, and wherein an angle between the guide wall of the pre-diffuser and the inlet extender proximate the distal end is less than 90 degrees.
15. The gas turbine engine of claim 10 , wherein the pre-diffuser includes a guide wall defining the pre-diffuser, and wherein an angle between the guide wall of the pre-diffuser and the inlet extender proximate the distal end is equal to 90 degrees.
16. The gas turbine engine of claim 10 , further comprising:
an orifice located in the inlet extender fluidly connecting the first inner plenum and the second inner plenum; and
a ramp located opposite the orifice.
17. The gas turbine engine of claim 16 , wherein the ramp extends away from a radially inward wall of the diffuser case and towards the orifice.
18. The gas turbine engine of claim 16 , wherein the ramp is orientated at an angle relative to a radially inward wall of the diffuser case, the angle being less than 90 degrees as measured between the radially inward wall and an aft side of the ramp.