Thermal shields for gas turbine rotor
A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk A non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk A compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk.
1. A turbomachine comprising:
a rotor having an axis and a plurality of disks positioned adjacent to each other in an axial direction, each disk including opposing axially facing surfaces;
at least one row of blades positioned on each of the plurality of disks, each row of blades extending radially outward from a radially facing surface of a respective disk of the plurality of disks;
a circumferentially continuous ring structure defining a thermal barrier extending axially between and overlapping the radially facing surfaces of two adjacent disks of the plurality of disks;
a compliant element comprising an annular elastic element located between a radially inner circumferential portion of the ring structure and an axially extending flange structure of one of the two adjacent disks, wherein the ring structure has an outer axially extending rim, a radially inner foot portion forming the radially inner circumferential portion of the ring structure, and a radially extending web that is axially narrower than the foot portion and forms a connection between the rim and the foot portion wherein the compliant element movably supports the foot portion to the flange structure;
a retention plate structure detachably fastened to the disk to engage the foot portion for axially retaining the ring structure to the flange structure,
wherein the foot portion includes an axial extension for engagement with one of the axially facing surfaces of the plurality of disks,
wherein the axial extension forms an anti-rotation feature having circumferentially facing surfaces boated in engagement with cooperating circumferentially facing surfaces formed on a facing surface of the disk; and
axially extending aft passages through the compliant element providing passage of air between the foot portion and the flange structure, and the ring structure including an outer rim haying edges boated adjacent to edges of the blades, wherein a gap is defined between the adjacent edges of the outer rim and the blades for passage of a cooling air flow from a radially inner to a radially outer location relative to the outer rim.
2. The turbomachine of claim 1 , wherein the compliant element is a circular wave spring.
3. The turbomachine of claim 1 , wherein the disks are formed of a first material and the ring structure is formed of a second material, which shields the radially facing surfaces of the disks from the temperature of a hot gas passing through an axial gas flow path containing the blades, and the second material having a higher heat resistance than the first material.
4. The turbomachine of claim 1 , wherein the compliant element is located at one of:
between a radially inward facing side of the ring structure and a radially outward facing side of the flange structure; and
between a radially outward facing side of the ring structure and a radially inward facing side of the flange structure.