Helicopter with cross-flow fan

• US 9,409,643 B2
• Filed: 05/22/2014
• Issued: 08/09/2016
• Est. Priority Date: 05/30/2013
• Status: Active Grant

• Current Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Original Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Inventors: Mores, Sebastian, D'Alascio, Alessandro, Bebesel, Marius
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Rodriguez, Vicente
• Application Number:
  US14/284,956
• Publication Number:
  US 20150191245A1
• Time in Patent Office: 810 Days
• Field of Search: 244/17.19
• US Class Current: 1/1
• CPC Class Codes: B64C 2027/8245 using air jets
• 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

Abstract

A helicopter with a fuselage (4), at least one engine, a roll axis, at least one main rotor, and at least one housing (2) mounted to said fuselage (4). An air inlet (8) and an air outlet (7) are provided along at least a part of a circumference of the at least one housing (2), said air inlet (8) and said air outlet (7) being formed by angularly offset and separate gaps between an inside segment (33) and an outside segment (34) essentially extending respectively longitudinally in direction of said roll axis. At least one rotatable compressor (1) with a plurality of airfoil blades (6) is provided radial inside said at least one housing (2) between said air inlet (8) and said air outlet (7), said at least one rotatable compressor (1) being drivable by said at least one engine about a fan axis (5) and each chord of said airfoil blades (6) is essentially radial oriented with regard to said fan axis (5).

Claims

1. A helicopter comprising:

a fuselage having a roll axis extending longitudinally, and at least one driving unit disposed in the fuselage;

at least one main rotor mounted to the fuselage and drivable by the at least one driving unit to rotate about a yaw axis perpendicular to the roll axis;

a cross-flow fan housing mounted to the fuselage extending essentially in the direction of the roll axis with an offset relative to the yaw axis; and

an air inlet for incoming air and an air outlet for outgoing air are provided along at least a part of a circumference of the fan housing, the air inlet and the air outlet being formed by angularly offset and separate gaps between an inside segment and an outside segment essentially extending in the direction of the roll axis; and

at least one rotatable compressor provided with a plurality of airfoil blades oriented radially about a fan axis inside the fan housing, the at least one rotatable compressor being drivable by the at least one driving unit;

wherein operation of the at least one rotatable compressor within the fan housing is configured to produce;

lift oriented from the air inlet in a lift direction opposite to a flow direction of the incoming air due to ingestion of the incoming air into the at least one rotatable compressor, and

lateral thrust oriented from the air outlet in a lateral thrust direction opposite to a flow direction of the outgoing air for anti-torque,

wherein the cross-flow fan housing is split into a front section, an aft section and a mid-section, the front section being closest to the yaw axis, the aft section being distal to the yaw axis and the mid-section being between the front section and the aft section, the front section, the aft section and the mid-section being separately and independently from each other pivotable about the fan axis.

2. The helicopter according to claim 1, wherein the inside segment and the outside segment of the fan housing are pivotable around the fan axis.

3. The helicopter according to claim 2, wherein remote control means are provided for remote control of an angular position of the inside segment and the outside segment of the housing.

4. The helicopter according to claim 1, wherein the air outlet has a diffusor shape.

5. The helicopter according to claim 1, wherein an output shaft is provided from a main gear box and the rotatable compressor is driven by the output shaft.

6. The helicopter according to claim 1, further comprising auxiliary forward propelling devices, wherein the rotatable compressor is adapted to drive the auxiliary forward propelling devices.

7. The helicopter according to claim 1, further comprising two cross-flow fans, each with the rotating compressor and cross-flow fan housing, the two cross-flow fans mounted parallel to each other and symmetric to a midplane on the fuselage.

8. The helicopter according to claim 1, wherein a width of the air inlet is greater than a width of the air outlet.

9. The helicopter according to claim 1, wherein the angular offset varies from 10°

to 90°

for an angle measured between a side from the fan axis to a lateral inlet delimitation of the air inlet and a side to a lateral outlet delimitation of the air outlet next to the lateral inlet delimitation of the air inlet.

10. The helicopter according to claim 1, wherein an angle about the fan axis from lateral inlet delimitations of the air inlet in an azimuth direction relative to the yaw axis vary for the lateral inlet delimitation between 350°

+/−

50° and

between 10°

+/−

50°

to the opposed lateral inlet delimitation with the yaw axis directed to the main rotor corresponding to 0° and

the degrees positive in clockwise direction.

11. The helicopter according to claim 10, wherein an angle about the fan axis from lateral outlet delimitations of the air outlet in an azimuth direction relative to the yaw axis vary on the lateral outlet delimitation between 215°

+/−

50° and

between 255°

+/−

50°

to the opposed lateral outlet delimitation.

12. The helicopter according to claim 1, wherein the inside segment and outside segment have different lengths, the air inlet and air outlet.

13. A cross-flow fan for a helicopter having a fuselage extending lengthwise in a longitudinal direction and having a rotor rotating about a yaw axis being perpendicular to the longitudinal direction, the cross-flow fan comprising:

a fan housing adapted to be pivotally mounted to the fuselage and having a fan axis extending in the longitudinal direction,

a rotatable compressor provided inside the fan housing and having a plurality of airfoil blades extending radially from and rotating about the fan axis; and

an air inlet provided along a first part of a circumference of the fan housing and an air outlet provided along a second part of the circumference of the fan housing provided at an angular offset from the air inlet and;

wherein the fan housing pivots thereby changing an angular position of the air inlet and air outlet to produce;

lift oriented from the air inlet in a lift direction opposite to a flow of incoming air into the air inlet, and

lateral thrust oriented from the air outlet in a lateral thrust direction opposite to a flow of outgoing air from the air outlet for anti-torque,

wherein the cross-flow fan housing is split into a front section, an aft section and a mid-section, the front section being closest to the yaw axis, the aft section being distal to the yaw axis and the mid-section being between the front section and the aft section, the front section, the aft section and the mid-section being separately and independently from each other pivotable about the fan axis.

14. The cross-flow fan according to claim 13, wherein the fan housing includes an inside segment and an outside segment both disposed along the circumference of the fan housing and oriented between the air inlet and the air outlet to provide the angular offset, the outside segment having a circumferential length greater than the inside segment.

15. The cross-flow fan according to claim 13, wherein the angular position of the air inlet and air outlet is controllable remotely by pivoting the fan housing, thereby varying the lift direction and the lateral thrust direction.

16. The cross-flow fan according to claim 13, wherein the first part of the circumference that defines a width of the air inlet is greater than the second part of the circumference that defines a width of the air outlet.

17. The cross-flow fan according to claim 13, wherein the angular offset is not 180°

.

18. A helicopter comprising:

a fuselage having a roll axis extending in a longitudinal direction,

at least one main rotor mounted to the fuselage to rotate about a yaw axis perpendicular to the roll axis;

a cross-flow fan housing pivotally mounted to the fuselage and having a fan axis extending in the longitudinal direction, the fan housing having a front section, an aft section and a mid section positioned longitudinally between the front section and the aft section, each of the aft section, the front section, and the mid section being pivotally mounted about the fan axis;

a rotatable compressor provided inside the fan housing and having a plurality of airfoil blades extending radially from and rotating about the fan axis; and

an air inlet and an air outlet extending longitudinally along each of the front section, aft section and mid section, wherein the air inlet is angularly offset along a circumference of the cross-flow fan housing from the air outlet,

wherein angular positions of the air inlet and the air outlet of each of the aft section, the front section, and the mid section is adapted to be varied with respect to each other when each of the aft section, the front section, and the mid section are pivoted.

19. The helicopter according to claim 18, wherein the fan housing includes an inside segment and an outside segment both disposed along the circumference of the fan housing and oriented between the air inlet and the air outlet to provide the angular offset, the outside segment having a circumferential length greater than the inside segment.