Rotorcraft variable thrust cross-flow fan systems

• US 10,279,900 B2
• Filed: 08/10/2016
• Issued: 05/07/2019
• Est. Priority Date: 08/10/2016
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Robertson, Daniel Bryan, Smith, Dudley, Dreier, Mark, Ivans, Steve Ray, Groninga, Kirk Landon
• Primary Examiner(s): McFall, Nicholas
• Application Number:
  US15/233,897
• Publication Number:
  US 20180044009A1
• Time in Patent Office: 1,000 Days
• CPC Class Codes: B64C 11/006 Paddle wheels
• CPC Class Codes: B64C 2027/8245 using air jets
• CPC Class Codes: B64C 2027/8254 Shrouded tail rotors, e.g. "Fenestron" fans
• CPC Class Codes: B64C 27/06 with single rotor
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
• CPC Class Codes: B64C 39/008 about a longitudinal axis
• CPC Class Codes: F04D 17/04 of transverse-flow type
• CPC Class Codes: F04D 29/283 rotors of the squirrel-cage type
• CPC Class Codes: F04D 29/287 with adjusting means
• CPC Class Codes: F04D 29/30 Vanes
• CPC Class Codes: F04D 29/362 during rotation
• CPC Class Codes: F05D 2220/90 in vehicles adapted for vertical or short take off and landing (v/stol vehicles)

Abstract

In some embodiments, a rotorcraft includes a fuselage, a tailboom, a drive system and a variable thrust cross-flow fan system. The cross-flow fan system includes a cross-flow fan assembly that is mechanically coupled to a drive shaft and operable to rotate with the drive shaft about a longitudinal axis. The cross-flow fan assembly includes first and second driver plates having a plurality of blades rotatably mounted therebetween. The blades are disposed radially outwardly from the longitudinal axis and have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis. The blades are moveable between a plurality of pitch angle configurations. A control assembly is coupled to the blades. The control assembly is operable to change the pitch angle configuration of the blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly.

Claims

1. A variable thrust cross-flow fan system for a rotorcraft, the system comprising:

a cross-flow fan assembly having a longitudinal axis and including first and second driver plates having a plurality of blades rotatably mounted therebetween, the plurality of blades disposed radially outwardly from the longitudinal axis such that the plurality of blades have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis, the plurality of blades moveable between a plurality of pitch angle configurations;

a control assembly coupled to the plurality of blades, the control assembly including a control cam operable to translate relative to the cross-flow fan assembly to change the pitch angle configuration of the plurality of blades; and

an actuator assembly operably coupled to the control cam, the actuator assembly operable to translate the control cam relative to the cross-flow fan assembly to change the pitch angle configuration of the plurality of blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly;

wherein the cross-flow fan assembly is operable to produce a thrust in one of a first or second direction in response to the actuator assembly translating the control cam leftward relative to the cross-flow fan assembly and is further operable to produce a thrust in the other of the first or second direction in response to the actuator assembly translating the control cam rightward relative to the cross-flow fan assembly, the first direction substantially opposite from the second direction.

2. The variable thrust cross-flow fan system as recited in claim 1 wherein the control cam is operable to rotate relative to the cross-flow fan assembly.

3. The variable thrust cross-flow fan system as recited in claim 1 wherein the control cam is substantially non-rotatable relative to the cross-flow fan assembly.

4. The variable thrust cross-flow fan system as recited in claim 1 wherein the control assembly further comprises a plurality of linkages, the control cam coupled to the plurality of blades by the plurality of linkages wherein each of the plurality of linkages has an inner end and an outer end, the inner end of each of the plurality of linkages slidably coupled to the control cam, the outer end of each of the plurality of linkages fixedly coupled to one of the plurality of blades.

5. The variable thrust cross-flow fan system as recited in claim 4 wherein the control cam forms at least one follower slot;

wherein the inner end of each of the plurality of linkages includes a follower pin; and

wherein the follower pin of each of the plurality of linkages is slidably engaged with the at least one follower slot.

6. The variable thrust cross-flow fan system as recited in claim 4 wherein the control cam forms a plurality of follower slots;

wherein the inner end of each of the plurality of linkages includes a follower pin; and

wherein the follower pin of each of the plurality of linkages is slidably engaged with one of the plurality of follower slots.

7. The variable thrust cross-flow fan system as recited in claim 1 wherein the plurality of pitch angle configurations includes at least one right thrust configuration, a neutral configuration and at least one left thrust configuration.

8. The variable thrust cross-flow fan system as recited in claim 1 wherein the plurality of pitch angle configurations includes a plurality of anti-torque thrust configurations.

9. The variable thrust cross-flow fan system as recited in claim 1 wherein the plurality of pitch angle configurations includes a plurality of pro-torque thrust configurations.

10. The variable thrust cross-flow fan system as recited in claim 1 wherein the plurality of pitch angle configurations includes pitch angle configurations wherein each of the plurality of blades changes pitch angle during each revolution around the generally circular path of travel.

11. The variable thrust cross-flow fan system as recited in claim 1 wherein the plurality of pitch angle configurations includes pitch angle configurations wherein each of the plurality of blades fluctuates between a positive pitch angle and a negative pitch angle during each revolution around the generally circular path of travel.

12. The variable thrust cross-flow fan system as recited in claim 11 wherein the plurality of pitch angle configurations includes pitch angle configurations wherein one or more blades of the plurality of blades has the negative pitch angle while one or more blades of the plurality of blades has the positive pitch angle.

13. The variable thrust cross-flow fan system as recited in claim 1 wherein the variable thrust is a reversible thrust.

14. The variable thrust cross-flow fan system as recited in claim 1 wherein the control cam forms one or more concentric follower slots.

15. The variable thrust cross-flow fan system as recited in claim 14 wherein the control assembly further comprises a plurality of linkages coupled to the plurality of blades and slidably engaged with the one or more concentric follower slots, the one or more concentric follower slots operable to translate relative to the cross-flow fan assembly, in response to translation of the control cam, to change the pitch angle configuration of the plurality of blades.

16. A rotorcraft, comprising:

a fuselage;

a tailboom extending from the fuselage, the tailboom having an aft portion;

a drive system having an engine, transmission and a drive shaft extending at least partially within the tailboom; and

a variable thrust cross-flow fan system located at the aft portion of the tailboom, the variable thrust cross-flow fan system including;

a cross-flow fan assembly mechanically coupled to the drive shaft and operable to rotate with the drive shaft about a longitudinal axis, the cross-flow fan assembly including first and second driver plates having a plurality of blades rotatably mounted therebetween, the plurality of blades disposed radially outwardly from the longitudinal axis such that the plurality of blades have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis, the plurality of blades moveable between a plurality of pitch angle configurations;

a control assembly coupled to the plurality of blades, the control assembly including a control cam operable to translate relative to the cross-flow fan assembly to change the pitch angle configuration of the plurality of blades; and

an actuator assembly operably coupled to the control cam, the actuator assembly operable to translate the control cam relative to the cross-flow fan assembly to change the pitch angle configuration of the plurality of blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly;

wherein the cross-flow fan assembly is operable to produce a thrust in one of a first or second direction in response to the actuator assembly translating the control cam leftward relative to the cross-flow fan assembly and is further operable to produce a thrust in the other of the first or second direction in response to the actuator assembly translating the control cam rightward relative to the cross-flow fan assembly, the first direction substantially opposite from the second direction.

17. The rotorcraft as recited in claim 16 wherein the variable thrust cross-flow fan system provides anti-torque thrust for the rotorcraft.

18. The rotorcraft as recited in claim 16 wherein the variable thrust cross-flow fan system provides yaw control thrust for the rotorcraft.

19. The rotorcraft as recited in claim 16 wherein the plurality of pitch angle configurations includes a plurality of anti-torque thrust configurations, a neutral configuration and a plurality of pro-torque thrust configurations.