Midshaft rating for turbomachine engines

Patent metadata

Field	Value
Publication number	US-11603801-B2
Application number	US-202117328795-A
Country	US
Kind code	B2
Filing date	May 24, 2021
Priority date	May 24, 2021
Publication date	Mar 14, 2023
Grant date	Mar 14, 2023

Abstract

A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.

First claim

The invention claimed is:

1. A turbomachine engine comprising:
a core engine including one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections; and
a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec) 1/2 and three hundred (ft/sec) 1/2 ,
wherein the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec), and
wherein the turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the shaft.

2. The turbomachine engine of claim 1 , wherein the MSR is between two hundred (ft/sec) 1/2 and two hundred forty-five (ft/sec) 1/2 .

3. The turbomachine engine of claim 1 , wherein the MSR is between two hundred twelve (ft/sec) 1/2 and two hundred sixty (ft/sec) 1/2 .

4. The turbomachine engine of claim 1 , wherein the MSR is between two hundred forty-seven (ft/sec) 1/2 and two hundred ninety (ft/sec) 1/2 .

5. The turbomachine engine of claim 1 , wherein the redline speed is between sixty and ninety ft/sec.

6. The turbomachine engine of claim 1 , wherein the redline speed is between seventy-five and one hundred seventy-five ft/sec.

7. The turbomachine engine of claim 1 , wherein the redline speed is between one hundred fifty and two hundred fifty ft/sec.

8. The turbomachine engine of claim 1 , wherein the shaft is a composite shaft made of at least two different materials.

9. The turbomachine engine of claim 1 , wherein the shaft has a length L and a reduced mass density at a midpoint along the length L.

10. The turbomachine engine of claim 9 , wherein the shaft is a hollow convex shaft with a reduced wall thickness at the midpoint, a variable inner diameter, and a constant outer diameter.

11. The turbomachine engine of claim 9 , wherein the shaft is a hollow convex shaft with a reduced wall thickness at the midpoint, a constant inner diameter, and a variable outer diameter.

12. The turbomachine engine of claim 1 , wherein the shaft is coupled to the power turbine at a first mounting point, and wherein the shaft is also coupled to one of the compressor sections at a second mounting point.

13. The turbomachine engine of claim 12 , wherein the shaft is supported by at least a first bearing and a second bearing.

14. The turbomachine engine of claim 13 , wherein the shaft has a length L that is measured as a distance between the first bearing and the second bearing.

15. The turbomachine engine of claim 13 , wherein the first bearing, the second bearing, or each of the first bearing and the second bearing is a duplex bearing having an overturning moment capability.

16. The turbomachine engine of claim 13 , wherein each bearing is one of a ball bearing and a roller bearing.

17. The turbomachine engine of claim 13 , wherein the first bearing is positioned between the first mounting point and the second mounting point, and wherein the second mounting point is positioned between the first bearing and the second bearing.

18. The turbomachine engine of claim 13 , wherein the first bearing and the second bearing support the shaft in an inbound configuration in which the first bearing and the second bearing are positioned between the first mounting point and the second mounting point.

19. The turbomachine engine of claim 13 , wherein the first bearing and the second bearing support the shaft in an outbound configuration in which the first mounting point and the second mounting point are positioned between the first bearing and the second bearing.

20. The turbomachine engine of claim 13 , wherein the shaft is further supported by a third bearing and a fourth bearing.

21. The turbomachine engine of claim 20 , wherein the first bearing and the second bearing are a first pair of duplex bearings, and the third bearing and the fourth bearing are a second pair of duplex bearings, wherein the first pair of duplex bearings and the second pair of duplex bearings support the shaft in an inbound overturning moment configuration in which the first pair of duplex bearings and the second pair of duplex bearings are positioned between the first mounting point and the second mounting point.

22. The turbomachine engine of claim 20 , wherein the first bearing and the second bearing are a first pair of duplex bearings, and the third bearing and the fourth bearing are a second pair of duplex bearings, wherein the first pair of duplex bearings and the second pair of duplex bearings support the shaft in an outbound overturning moment configuration in which the first mounting point and the second mounting point are positioned between the first pair of duplex bearings and the second pair of duplex bearings.

23. The turbomachine engine of claim 20 , wherein the first bearing, the second bearing, the third bearing, and the fourth bearing support the shaft in a four-bearing straddle configuration in which the first bearing and the second bearing are positioned between the first mounting point and the second mounting point, and the first mounting point and the second mounting point are positioned between the third bearing and the fourth bearing.

24. The turbomachine engine of claim 20 , wherein the first bearing, the second bearing, the third bearing, and the fourth bearing support the shaft in a four-bearing outbound configuration in which the first mounting point and the second mounting point are positioned between a first group of bearings comprising the first bearing and the second bearing, and a second group of bearings comprising the third bearing and the fourth bearing.

Assignees

• Gen Electric

Inventors

• Payyoor Narayanan
• Kang Weize
• Becker Thomas Lee
• Schmidt Richard

Classifications

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F01D25/16

  Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/54

  Radial bearings · CPC title

• F02C7/06 Primary

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title