Inserts for slotted integrally bladed rotor
Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.
1. An integrally bladed rotor comprising:
a central hub;
an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms;
a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms;
a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim; and
a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor,
wherein the rotor slot insert comprises an integral stop configured to engage with the first side of the central hub.
2. The integrally bladed rotor of claim 1 , wherein each of the rotor slot and the rotor slot insert have a dovetail geometry.
3. The integrally bladed rotor of claim 1 , wherein the rotor slot insert comprises a locking slot, the integrally bladed rotor further comprising a retaining element configured to engage with the locking slot, wherein the retaining element secures the rotor slot insert to the integrally bladed rotor on the second side of the central hub.
4. The integrally bladed rotor of claim 3 , wherein the retaining element is a retainer ring.
5. The integrally bladed rotor of claim 1 , wherein each of the rotor slot and the rotor slot insert has straight sidewalls, wherein the integrally bladed rotor further comprises an axial retaining element configured to secure the rotor slot insert to the integrally bladed rotor in an axial direction and a radially retaining element configured to secure the rotor slot insert to the integrally bladed rotor in a radial direction.
6. The integrally bladed rotor of claim 1 , wherein the rotor slot insert is hollow.
7. The integrally bladed rotor of claim 1 , wherein the rotor slot insert comprises a first material defining an exterior shell.
8. The integrally bladed rotor of claim 7 , further comprising a second material within the exterior shell, wherein the second material is different from the first material.
9. The integrally bladed rotor of claim 7 , wherein the exterior shell is filled with a gas or contains a vacuum.
10. The integrally bladed rotor of claim 1 , wherein the rotor slot insert is formed of a material that is different than a material of the integrally bladed rotor.
11. The integrally bladed rotor of claim 10 , wherein the material of the rotor slot insert is a softer material than the material of the integrally bladed rotor.
12. The integrally bladed rotor of claim 1 , wherein the rotor slot insert is formed from a material selected from a nickel-base alloy, a titanium-base alloy, a cobalt-base alloy, an iron-base alloy, a steel alloy, an aluminum-base alloy, a magnesium-base alloy, a columbium-base alloy, a nickel-copper alloy, a copper alloy, a ceramic material, and a composite material.
13. The integrally bladed rotor of claim 1 , wherein the rotor slot insert forms an interference fit with the integrally bladed rotor within the rotor slot.
14. The integrally bladed rotor of claim 1 , wherein the rotor slot insert comprises a material having a higher coefficient of thermal expansion than a material of the integrally bladed rotor to create an interference fit therebetween during operation of the integrally bladed rotor due to thermal expansion of the rotor slot insert.
15. The integrally bladed rotor of claim 1 , further comprising:
a plurality of additional rotor slots such that one rotor slot is arranged between each pair of blades of the integrally bladed rotor; and
a plurality of additional rotor slot inserts arranged such that each rotor slot includes a rotor slot insert installed therein.
16. A gas turbine engine comprising:
an integrally bladed rotor having a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor,
wherein each of the rotor slot and the rotor slot insert has straight sidewalls, wherein the integrally bladed rotor further comprises an axial retaining element configured to secure the rotor slot insert to the integrally bladed rotor in an axial direction and a radially retaining element configured to secure the rotor slot insert to the integrally bladed rotor in a radial direction.
17. The gas turbine engine of claim 16 , further comprising:
a plurality of additional rotor slots such that one rotor slot is arranged between each pair of blades of the integrally bladed rotor; and
a plurality of additional rotor slot inserts arranged such that each rotor slot includes a rotor slot insert installed therein.
18. The gas turbine engine of claim 16 , further comprising a plurality of additional integrally bladed rotors.
19. The gas turbine engine of claim 16 , the gas turbine engine comprising a high pressure compressor, wherein the integrally bladed rotor is a rotor of the high pressure compressor.
20. An integrally bladed rotor comprising:
a central hub;
an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms;
a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms;
a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim; and
a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor,
wherein the rotor slot insert comprises a first material defining an exterior shell and the exterior shell is filled with a gas or contains a vacuum.