SPLIT VERNIER RING FOR TURBINE ROTOR STACK ASSEMBLY

• US 20200131910A1
• Filed: 10/31/2018
• Published: 04/30/2020
• Est. Priority Date: 10/31/2018
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Juh, Christopher M., Virkler, Scott D.
• Granted Patent: US 11,021,958 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 5/025 Fixing blade carrying members on shafts attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00
• CPC Class Codes: F01D 5/026 Shaft to shaft connections
• CPC Class Codes: F01D 5/06 Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections F01D5/022, F01D5/023 take precedence
• CPC Class Codes: F01D 5/066 Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A power turbine rotor assembly including a rotor shaft. The assembly also includes a rotor stack surrounding the rotor shaft. The assembly further includes a nut axially retaining the rotor stack. The assembly yet further includes a Vernier ring engaged with the nut and the rotor shaft, the Vernier ring having an inner ring, a plurality of inner tabs extending radially inward from the inner ring, and a plurality of outer tabs extending radially outward from the inner ring, the Vernier ring formed of at least two ring segments.

Claims

1. A power turbine rotor assembly comprising:

a rotor shaft;

a rotor stack surrounding the rotor shaft;

nut axially retaining the rotor stack; and

a Vernier ring engaged with the nut and the rotor shaft, the Vernier ring having an inner ring, a plurality of inner tabs extending radially inward from the inner ring, and a plurality of outer tabs extending radially outward from the inner ring, the Vernier ring formed of at least two ring segments.

2. The power turbine rotor assembly of claim 1, further comprising an outer ring, the plurality of outer tabs extending between, and connecting, the inner ring and the outer ring.

3. The power turbine rotor assembly of claim 1, wherein each of the plurality of inner tabs are disposed within one of a plurality of corresponding slots defined by the rotor shaft.

4. The power turbine rotor assembly of claim 1, wherein each of the plurality of outer tabs are disposed between adjacent protrusions extending from the nut.

5. The power turbine rotor assembly of claim 4, wherein the inner ring, the outer ring, and adjacent outer tabs define a plurality of windows of the Vernier ring, each of the protrusions of the nut disposed within one of the plurality of windows.

6. The power turbine rotor assembly of claim 1, wherein the power turbine rotor assembly is disposed on a helicopter.

7. A Vernier ring comprising:

an inner ring;

an outer ring;

a plurality of inner tabs extending radially inward from the inner ring, the inner tabs circumferentially spaced from each other; and

a plurality of outer tabs extending between, and connecting, the inner ring and the outer ring, the Vernier ring formed of at least two ring segments.

8. The Vernier ring of claim 7, wherein the Vernier ring is disposed on a helicopter.

9. The Vernier ring of claim 7, wherein the wherein the inner ring, the outer ring, and adjacent outer tabs define a plurality of windows.

10. A gas turbine engine comprising:

a gas generator turbine section; and

a power turbine section arranged fluidly downstream from the gas generator turbine section, the power turbine mechanically disconnected from the gas generator portion, the power turbine comprising;

a rotor shaft;

a rotor stack surrounding the rotor shaft;

a nut axially retaining the rotor stack; and

a Vernier ring engaged with the nut and the rotor shaft, the Vernier ring having an inner ring, a plurality of inner tabs extending radially inward from the inner ring, and a plurality of outer tabs extending radially outward from the inner ring, the Vernier ring formed of at least two ring segments.

11. The gas turbine engine of claim 10, further comprising an outer ring, the plurality of outer tabs extending between, and connecting, the inner ring and the outer ring.

12. The gas turbine engine of claim 10, wherein each of the plurality of inner tabs are disposed within one of a plurality of corresponding slots defined by the rotor shaft.

13. The gas turbine engine of claim 10, wherein each of the plurality of outer tabs are disposed between adjacent protrusions extending from the nut.

14. The gas turbine engine of claim 13, wherein the inner ring, the outer ring, and adjacent outer tabs define a plurality of windows of the Vernier ring, each of the protrusions of the nut disposed within one of the plurality of windows.

15. The gas turbine engine of claim 10, wherein the power turbine rotor assembly is disposed on a helicopter.

16. The gas turbine engine of claim 10, wherein the Vernier ring is disposed in a high pressure turbine section of the gas turbine engine.

17. The gas turbine engine of claim 10, wherein the Vernier ring is disposed in an intermediate pressure turbine section of the gas turbine engine.

18. The gas turbine engine of claim 10, wherein the Vernier ring is disposed in a low pressure turbine section of the gas turbine engine.

19. The gas turbine engine of claim 10, wherein the Vernier ring is disposed in a compressor section of the gas turbine engine.

20. The gas turbine engine of claim 10, wherein the power turbine section is disposed in an aircraft.