Pre-diffuser strut for gas turbine engine
A pre-diffuser of an inner diffuser case of a gas turbine engine may comprise an annular outer wall and an annular inner wall radially inside of the annular outer wall to define a passage for primary airflow therebetween. The pre-diffuser may further comprise at least one strut extending radially between the annular inner wall and the annular outer wall and at least one aperture formed in the strut that extends radially through the strut, the annular inner wall, and the annular outer wall. The pre-diffuser may further comprise at least one hollow cavity formed in the strut, and the hollow cavity may be separate from the aperture.
1. A pre-diffuser of an inner diffuser case for a gas turbine engine, comprising:
an annular outer wall;
an annular inner wall radially inside of the annular outer wall, the annular outer wall and the annular inner wall defining a passage for primary airflow therebetween;
at least one strut extending radially between the annular inner wall and the annular outer wall;
at least one aperture formed in the at least one strut, the at least one aperture extending radially and completely through the at least one strut, the annular inner wall, and the annular outer wall to provide a secondary cooling airflow passage between a bearing compartment and an aft portion of a compressor section of the gas turbine engine;
at least one hollow cavity formed in the at least one strut, the at least one hollow cavity being separate from the at least one aperture; and
wherein the at least one strut includes a forward side upstream from an aft side, and wherein the at least one hollow cavity is aft of the at least one aperture on the aft side of the at least one strut.
2. The pre-diffuser of claim 1 , wherein the at least one strut includes a radially-extending wall separating the at least one aperture and the at least one hollow cavity.
3. The pre-diffuser of claim 2 , wherein the at least one strut includes two outer walls extending axially between the radially-extending wall and an open end on the aft side of the at least one strut, and wherein the two outer walls further extend radially between the annular inner wall and the annular outer wall.
4. The pre-diffuser of claim 3 , wherein the two outer walls define the at least one hollow cavity therebetween, and wherein the at least one hollow cavity includes the open end.
5. The pre-diffuser of claim 4 , wherein each of the two outer walls have an average wall thickness of between 1.5 millimeters and 2.3 millimeters.
6. The pre-diffuser of claim 4 , wherein the at least one strut comprises a plurality of the struts, and wherein each strut of the plurality of struts includes a respective aperture of the at least one aperture and a respective hollow cavity of the at least one hollow cavity.
7. The pre-diffuser of claim 6 , wherein the pre-diffuser is cast using a mold.
8. The pre-diffuser of claim 6 , wherein the plurality of apertures and the plurality of hollow cavities are formed by machining.
9. The pre-diffuser of claim 1 , wherein the annular inner wall and the annular outer wall diverge radially with respect to each other from an inlet of the passage to an outlet of the passage.
10. A gas turbine engine, comprising:
a fan section;
a core engine downstream of the fan section and including a compressor section, a combustor, and a turbine section; and
a diffuser case at an outlet of the compressor section and having an annular outer diffuser case and an annular inner diffuser case radially inside of the annular outer diffuser case, the annular inner diffuser case having a pre-diffuser at an upstream portion of the annular inner diffuser case, the pre-diffuser including
an annular outer wall,
an annular inner wall radially inside of the annular outer wall, the annular outer wall and the annular inner wall defining a passage for primary airflow therebetween,
at least one strut extending radially between the annular inner wall and the annular outer wall,
at least one aperture formed in the at least one strut, the at least one aperture extending radially and completely through the at least one strut, the annular inner wall, and the annular outer wall to provide a secondary cooling airflow passage between a bearing compartment and an aft portion of the compressor section of the gas turbine engine,
at least one hollow cavity formed in the at least one strut, the at least one hollow cavity being separate from the at least one aperture, and
wherein the at least one strut includes a forward side upstream from an aft side, and wherein the at least one hollow cavity is aft of the at least one aperture on the aft side of the at least one strut.
11. The gas turbine engine of claim 10 , wherein the at least one strut includes a radially-extending wall separating the at least one aperture and the at least one hollow cavity.
12. The gas turbine engine of claim 11 , wherein the at least one strut includes two outer walls extending axially between the radially-extending wall and an open end on the aft side of the at least one strut, and wherein the two outer walls further extend radially between the annular inner wall and the annular outer wall.
13. The gas turbine engine of claim 12 , wherein the two outer walls define the at least one hollow cavity therebetween, and wherein the at least one hollow cavity includes the open end.
14. The gas turbine engine of claim 13 , wherein each of the two outer walls have an average wall thickness of between 1.5 millimeters and 2.3 millimeters.
15. The gas turbine engine of claim 12 , wherein the at least one strut comprises a plurality of the struts, wherein each strut of the plurality of struts includes a respective aperture of the at least one aperture and a respective hollow cavity of the at least one hollow cavity.
16. The gas turbine of claim 10 , wherein the annular inner wall and the annular outer wall diverge radially with respect to each other from an inlet of the passage to an outlet of the passage.