Granted Patent B2

US 12,601,271 · App. 17/970,687 · Granted Apr 14, 2026

Inventors: Abhijeet Jayshingrao Yadav (Karad, IN); Nicholas Joseph Kray (Mason, OH); Nicholas M. Daggett (Camden, ME); Nitesh Jain (Bengaluru, IN); Matthew Mark Weaver (Loveland, OH); Srinivas Addagatla (Gebze, TR)

Assignee: General Electric Company

F01D7/00F04D29/323F04D29/362F05D2220/323F05D2220/36F05D2240/30F05D2260/36F05D2260/74F05D2260/75F05D2260/76F05D2260/77F05D2260/79

Abstract

Claims (37)

1 . A gas turbine engine comprising:

a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order;

a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis and a disk;

a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades;

a counterweight connected to each respective fan blade; and

a spring mechanism operably associated with each respective fan blade, the spring mechanism of each respective fan blade operable to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade, wherein the spring mechanism comprises a non-linear spring;

wherein each respective fan blade is coupled to a respective trunnion comprising a respective sleeve, wherein the non-linear spring of the spring mechanism is wrapped about the respective sleeve of the respective trunnion, and wherein the non-linear spring comprises a first end directly coupled to the disk and a second end directly coupled to the respective trunnion of each respective fan blade.

2 . The gas turbine engine of claim 1 , wherein the non-linear spring comprises a torsion spring.

3 . The gas turbine engine of claim 1 , wherein the respective trunnion of each respective fan blade includes a cam portion, and wherein the spring mechanism includes a biased follower operatively engageable with the respective cam portion.

4 . The gas turbine engine of claim 1 , wherein the respective trunnion of each respective fan blade includes a gear portion, and wherein the spring mechanism includes a biased gear engageable with the respective gear portion.

5 . The gas turbine engine of claim 1 , wherein the counterweight is rotatable about a hub, and wherein the non-linear spring comprises a torsion spring wound around the hub.

6 . The gas turbine engine of claim 1 , wherein:

the spring mechanism defines an annular gap between an inner wall of the disk and the respective sleeve of the respective trunnion; and

the non-linear spring of the spring mechanism is disposed within the annular gap.

7 . The gas turbine engine of claim 1 , wherein the counterweight is operably coupled to the respective trunnion of each respective fan blade.

8 . The gas turbine engine of claim 1 , further comprising a link arm coupled to the respective trunnion via linkages, a lever arm coupled to and extending between the link arm and the counterweight, wherein the lever arm is configured to transfer movement of the counterweight to the link arm to drive rotation of the respective trunnion relative to the disk.

9 . A gas turbine engine comprising:

a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order;

a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis and a disk;

a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades;

a counterweight connected to each respective fan blade; and

a spring mechanism operably associated with each respective fan blade, the spring mechanism operable with the counterweight of each respective fan blade to counter a centrifugal twisting moment of each respective fan blade, wherein the spring mechanism comprises a non-linear spring;

wherein each respective fan blade is coupled to a respective trunnion comprising a respective sleeve, and wherein the non-linear spring of the spring mechanism is wrapped about the respective sleeve of the respective trunnion, and wherein the non-linear spring comprises a first end directly coupled to the disk and a second end directly coupled to the respective trunnion of each respective fan blade.

10 . The gas turbine engine of claim 9 , wherein the non-linear spring comprises a torsion spring.

11 . The gas turbine engine of claim 9 , wherein the respective trunnion of each respective fan blade includes a cam portion, and wherein the spring mechanism comprises a biased follower operatively engageable with the respective cam portion.

12 . The gas turbine engine of claim 9 , wherein the respective trunnion of each respective fan blade includes a gear portion, and wherein the spring mechanism comprises a biased gear engageable with the respective gear portion.

13 . The gas turbine engine of claim 9 , wherein the counterweight is rotatable about a hub, and wherein the non-linear spring comprises a torsion spring wound around the hub.

14 . A gas turbine engine comprising:

a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order;

a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis and a disk;

a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades; and

a plurality of spring mechanisms, each spring mechanism of the plurality of spring mechanisms operably associated with each respective fan blade of the plurality of fan blades, each respective spring mechanism creating a spring twisting moment on the respective fan blade to counter a centrifugal twisting moment of the respective fan blade, wherein each spring mechanism of the plurality of spring mechanisms comprises a non-linear spring;

wherein each respective fan blade is coupled to a respective trunnion comprising a respective sleeve, and wherein the non-linear spring of each spring mechanism of the plurality of spring mechanisms is wrapped about the respective sleeve of the respective trunnion; and

wherein the non-linear spring comprises a first end directly coupled to the disk and a second end directly coupled to the respective trunnion of each respective fan blade.

15 . The gas turbine engine of claim 14 , wherein the respective trunnion of each respective fan blade includes a cam portion, and wherein each spring mechanism of the plurality of spring mechanisms comprises a spring-biased follower operatively engageable with the respective cam portion.

16 . The gas turbine engine of claim 14 , wherein the respective trunnion of each respective fan blade includes a gear portion, and wherein each spring mechanism of the plurality of spring mechanisms comprises a spring-biased gear engageable with the respective gear portion.

17 . The gas turbine engine of claim 14 , wherein the respective trunnion of each respective fan blade includes a cam portion, and wherein each spring mechanism of the plurality of spring mechanisms comprises a spring compressible by a plunger operatively engageable with the respective cam portion.

Assignments (1)

Continuity (2)

References Cited (400)