JET ENGINE ACTUATION SYSTEM

• US 20150275770A1
• Filed: 03/27/2014
• Published: 10/01/2015
• Est. Priority Date: 03/27/2014
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Emmons, Floyd Richard
• Granted Patent: US 9,617,922 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F02C 9/22 by adjusting turbine vanes
• CPC Class Codes: F16H 35/18 Turning devices for rotatable members, e.g. shafts
• CPC Class Codes: Y10T 74/18568 Reciprocating or oscillating to or from alternating rotary

Abstract

A jet engine actuation system includes a first ring gearbox, a second ring gearbox and an actuator. The first ring gearbox includes a first ring driveshaft coupled to a first portion of a synchronization ring included in a jet engine. The second ring gear box includes a second ring drive shaft coupled to a second portion of the synchronization ring. The actuator has a first actuator gearbox configured to generate a first rotational output and a second actuator gearbox configured to generate a second rotational output. A first drive shaft transfers the first rotational output to the first ring gearbox and a second drive shaft transfers the second rotational output to the second ring gearbox. The actuator simultaneously controls the first and second actuator gearboxes such that the first and second rotational outputs are simultaneously transferred to the first and second ring gearboxes to rotate the synchronization ring.

Claims

1. A jet engine system, comprising:

at least one engine including;

a synchronization ring configured to circumferentially rotate;

an inner housing that supports the synchronization ring;

an actuation system including;

first and second ring gearboxes coupled to the inner housing and configured to rotate the synchronization ring;

an actuator having a first gearbox configured to generate a first rotational output and a second actuator gearbox configured to generate a second rotational output;

a first drive shaft having a first shaft end rotatably coupled to the first actuator gearbox and a second shaft end rotatably coupled to the first ring gear box; and

a second drive shaft having a first shaft end rotatably coupled to the second actuator gearbox and the second shaft end rotatably coupled to the second ring gear box,

wherein the actuator is configured to simultaneously control the first and second actuator gearboxes such that the first and second rotational outputs are simultaneously transferred to the first and second ring gearboxes, respectively, to circumferentially rotate the synchronization ring.

2. The jet engine system of claim 1, wherein a first vertical axis extends through the first side of the synchronization ring and is perpendicular to the horizontal axis, and a second vertical axis extends through the second side of the synchronization ring and is perpendicular to the horizontal axis, the first and second vertical axes defining an exterior envelope region therebetween.

3. The system of claim 2, wherein the exterior envelope region has a length equal to the ring diameter.

4. The jet engine system of claim 3, wherein the actuator is disposed within the exterior envelope region.

5. The jet engine system of claim 4, further comprising an outer housing disposed about the inner housing;

wherein the actuator is coupled to an exterior surface of the outer housing.

8. The jet engine system of claim 5, wherein the body of the first and second drive shafts includes at least one curved portion between the first and second ends.

6. The jet engine system of 5, wherein the body of the first and second drive shafts is substantially straight between the first and second ends.

7. The jet engine system of claim 6, wherein each body extends between a respective actuator gearbox and a respective ring gearbox at an angle with respect to the exterior envelope.

9. The jet engine system of claim 7, wherein the first and second ring gearboxes are aligned with a horizontal axis extending radially through the inner housing.

10. The jet engine system of claim 9, wherein the first ring gearbox is coupled to a first side of the inner housing and the second ring gearbox is coupled to a second side of the inner housing opposite the first side, each of the first and second gearboxes including a ring shaft extending through the inner housing and rotatably coupled to a respective portion of the synchronization ring.

11. The jet engine system of claim 10, wherein the first drive shaft has a body disposed through a first hole formed in the outer housing and extends between first and second shaft ends, and the second drive shaft has a body disposed through a second hole formed in the outer housing and extends between first and second shaft ends.

12. The jet engine system of claim 11, further comprising a plurality of stator vanes rotatably coupled to the synchronization ring and extending radially from the synchronization ring into the air passage, the plurality of stator vanes configured to rotate in response to rotating the synchronization ring.

13. A jet engine actuation system, comprising:

a first ring gearbox including a first ring driveshaft coupled to a first portion of a synchronization ring included in a jet engine;

a second ring gear box including a second ring drive shaft coupled to a second portion of the synchronization ring, the first and second portions located opposite from one another and aligned along a horizontal axis extending radially through the synchronization ring;

an actuator having a first actuator gearbox configured to generate a first rotational output and a second actuator gearbox configured to generate a second rotational output;

a first drive shaft having a first end rotatably coupled to the first ring gearbox and a second end coupled the first actuator gearbox; and

a second drive shaft having a first end rotatably coupled to the second ring gearbox and a second end coupled the second actuator gearbox;

wherein the actuator is configured to simultaneously control the first and second actuator gearboxes such that the first and second rotational outputs are simultaneously transferred to the first and second ring gearboxes, respectively to circumferentially rotate the synchronization ring.

14. The jet actuation system of claim 13, wherein a first vertical axis extends through the first side of the synchronization ring and is perpendicular to the horizontal axis, and a second vertical axis extends through the second side of the synchronization ring and is perpendicular to the horizontal axis, the first and second vertical axes defining an exterior envelope region

15. The jet actuation system of claim 14, wherein the body of the first and second drive shafts is substantially straight between the first and second ends, and wherein each body extends between a respective actuator gearbox and a respective ring gearbox at an angle with respect to the exterior envelope.