Gas turbine engine case including bearing compartment
An example case for a gas turbine engine includes a bearing compartment, a radially outer ring, and a radially inner ring. The radially outer ring and radially inner ring are connected by a plurality of circumferentially spaced apart struts and define an annular flow path therebetween. The radially inner ring includes a first flange that extends radially outward from the bearing compartment. The first flange includes an undulation that extends axially away from the plurality of struts, and defines a load path between the bearing compartment and the radially outer ring.
1. A case for a gas turbine engine, comprising:
a bearing compartment; and
a radially outer ring and a radially inner ring connected by a plurality of circumferentially spaced apart struts and defining an annular flow path therebetween;
the radially inner ring comprising a first flange that extends radially outward from the bearing compartment, the first flange comprising an undulation that extends axially away from the plurality of struts, and defining a load path between the bearing compartment and the radially outer ring, the undulation including first and second undulation portions;
wherein the first undulation portion meets the radially extending portion at a first bend having a first radius of curvature, and extends with at least a component in an axial direction from the first bend to the apex;
wherein the first and second undulation portions meet at the apex at a second bend having a second radius of curvature that is less than the first radius of curvature; and
wherein the second undulation portion extends with at least a component in an axial direction from the second bend towards to the radially extending portion.
2. The case of claim 1 , comprising a plurality of oil lines, each oil line disposed within a respective one of the plurality of struts and in fluid communication with the bearing compartment.
3. The case of claim 1 , wherein the radially inner ring comprises a second flange that extends radially inward towards the bearing compartment, the plurality of struts are at least partially disposed between the first and second flanges, and the second flange moves freely relative to the bearing compartment.
4. The case of claim 3 , wherein the case is a turbine exhaust case and the second flange is aft of the first flange and is mounted to a heat shield that encloses an aft side of the bearing compartment.
5. The case of claim 3 , wherein the first flange is at least partially axially forward of the plurality of struts, and the second flange is at least partially axially aft of the plurality of struts.
6. The case of claim 5 , wherein the first flange includes a radially extending portion disposed between the undulation and the bearing compartment, and an apex of the undulation is axially forward of the radially extending portion.
7. The case of claim 3 , wherein:
the first flange is at least partially axially aft of the plurality of struts;
the second flange is at least partially axially forward of the plurality of struts;
the first flange includes a radially extending portion that extends between the undulation and the bearing compartment; and
an apex of the undulation is axially aft of the radially extending portion.
8. The case of claim 1 , wherein the radially inner ring comprises a second flange that extends radially outward from the bearing compartment, the plurality of struts at least partially disposed between the first and second flanges, the second flange comprising an undulation that extends axially away from the plurality of struts and defining an additional load path between the bearing compartment and the radially outer ring.
9. The case of claim 1 , wherein the first flange is integrally formed with the bearing compartment.
10. A gas turbine engine, comprising:
a core engine configured to compress and communicate airflow from a core flow path into a combustor section for expansion through a turbine section; and
a case comprising:
a bearing compartment; and
a radially outer ring and a radially inner ring connected by a plurality of circumferentially spaced apart struts and defining a portion of the core flow path therebetween;
the radially inner ring comprising a first flange that extends radially outward from the bearing compartment, the first flange comprising an undulation that extends axially away from the plurality of struts, and defining a load path between the bearing compartment and the radially outer ring, the undulation including first and second undulation portions;
wherein the first undulation portion meets the radially extending portion at a first bend having a first radius of curvature, and extends with at least a component in an axial direction from the first bend to the apex;
wherein the first and second undulation portions meet at the apex at a second bend having a second radius of curvature that is less than the first radius of curvature; and
wherein the second undulation portion extends with at least a component in an axial direction from the second bend towards to the radially extending portion.
11. The gas turbine engine of claim 10 , comprising:
a plurality of oil lines, each oil line disposed within a respective one of the plurality of struts; and
a lubrication system in fluid communication with the bearing compartment through the plurality of oil lines.
12. The gas turbine engine of claim 10 , wherein the radially inner ring comprises a second flange that extends radially inward towards the bearing compartment, the plurality of struts at least partially disposed between the first and second flanges, and the second flange moves freely relative to the bearing compartment.
13. The gas turbine engine of claim 10 , wherein the first flange is one of at least partially axially forward of the plurality of struts and at least partially axially aft of the plurality of struts, and the second flange is the other of at least partially axially forward of the plurality of struts and at least partially axially aft of the plurality of struts.
14. The gas turbine engine of claim 13 , wherein the case is a turbine exhaust case and the second flange is aft of the first flange and is mounted to a heat shield that encloses an aft side of the bearing compartment.
15. The gas turbine engine of claim 13 , wherein the first flange includes a radially extending portion disposed between the undulation and the bearing compartment, and an apex of the undulation is spaced axially away from the radially extending portion and the plurality of struts.
16. The gas turbine engine of claim 15 , wherein the undulation comprises first and second portions that meet at the apex, the first portion extends between the apex and the radially extending portion and is approximately parallel to a central longitudinal axis of the gas turbine engine, and the first and second portions are acutely angled with respect to each other.
17. The gas turbine engine of claim 10 , wherein the radially inner ring comprises a second flange that extends radially outward from the bearing compartment, the plurality of struts at least partially disposed between the first and second flanges, and the second flange comprising an undulation that extends axially away from the plurality of struts and defines an additional load path between the bearing compartment and the radially outer ring.
18. The gas turbine engine of claim 10 , wherein the bearing compartment comprises:
at least one first bearing that supports a high pressure spool; and
at least one second bearing that supports a low pressure spool;
wherein the high and low pressure spools rotate about a common axis.
19. A case for a gas turbine engine, comprising:
a bearing compartment; and
a radially outer ring and a radially inner ring connected by a plurality of circumferentially spaced apart struts and defining an annular flow path therebetween;
the radially inner ring comprising a first flange that extends radially outward from the bearing compartment, the first flange comprising an undulation that extends axially away from the plurality of struts, and defining a load path between the bearing compartment and the radially outer ring; and
a second flange that extends radially inward towards the bearing compartment, wherein the plurality of struts are at least partially disposed between the first and second flanges, and the second flange moves freely relative to the bearing compartment;
wherein:
the first flange is at least partially axially aft of the plurality of struts;
the second flange is at least partially axially forward of the plurality of struts;
the first flange includes a radially extending portion that extends between the undulation and the bearing compartment; and
an apex of the undulation is axially aft of the radially extending portion.
20. A case for a gas turbine engine, comprising:
a bearing compartment; and
a radially outer ring and a radially inner ring connected by a plurality of circumferentially spaced apart struts and defining an annular flow path therebetween;
the radially inner ring comprising a first flange that extends radially outward from the bearing compartment, the first flange comprising an undulation that extends axially away from the plurality of struts, and defining a load path between the bearing compartment and the radially outer ring;
wherein the radially inner ring comprises a second flange that extends radially outward from the bearing compartment, the plurality of struts at least partially disposed between the first and second flanges, the second flange comprising an undulation that extends axially away from the plurality of struts and defining an additional load path between the bearing compartment and the radially outer ring.