1. A dryer comprising:
a drum rotatably mounted in the interior of a main body;
a duct guiding air supplied to the drum;
a heater assembly provided within the duct and heating air supplied to the drum; and
a steam generator generating steam to be supplied to the drum by using heat generated by the heater assembly.
2. The dryer of claim 1, wherein the steam generator is a metal pipe bent zigzags near the heater assembly, and receives radiant heat and convective heat from the heater assembly.
3. The dryer of claim 2, wherein the steam generator is disposed in the vicinity of an air discharge portion of the heater assembly.
4. The dryer of claim 3, wherein the steam generator is formed to surround the heater assembly.
5. The dryer of claim 1, further comprising:
a steam hose having one end connected to the steam generator and guiding steam discharged from the steam generator; and
a nozzle provided at the other end of the steam hose and jetting steam to the drum.
6. The dryer of claim 5, wherein the steam hose is installed to be in contact with the duct.
7. The dryer of claim 1, wherein the steam generator is formed of an aluminum pipe or a copper pipe.
8. The dryer of claim 1, wherein the steam generator comprises a first generator disposed at an upper side of the heater assembly and a second generator disposed at a lower side of the heater assembly.
9. The dryer of claim 8, wherein the steam generator further comprises a third generator connecting the first and second generators and disposed to be adjacent to a side portion of the heater assembly.
10. The dryer of claim 9, wherein the third generator is disposed to be adjacent to a side portion of the heater assembly from which heated air is discharged.
11. The dryer of claim 8, wherein the steam generator further comprises an auxiliary generator disposed within the duct such that it is connected with the steam generator, and re-heating steam discharged from the steam generator.
12. The dryer of claim 11, wherein the auxiliary generator extends up to a discharge hole of the duct communicating with the drum along the duct, and a nozzle is mounted at the end of the auxiliary generator in order to jet steam to the interior of the drum from the discharge hole.
13. The dryer of claim 11, wherein the auxiliary generator is configured as a metal pipe extending elongatedly along the duct.
14. The dryer of claim 8, further comprising:
a steam hose connected to the steam generator and guiding steam discharged from the steam generator; and
a nozzle provided to the end of the steam hose and jetting steam to the interior of the drum.
15. The dryer of claim 14, wherein the nozzle is installed at a rear supporter rotatably supporting a rear end portion of the drum, or at the duct.
16. The dryer of claim 14, wherein the auxiliary generator extends up to the discharge hole of the duct communicating with the drum, and the nozzle is mounted at the end of the auxiliary generator to jet steam to the interior of the drum from the discharge hole.
17. The dryer of claim 1, further comprising:
a reservoir storing water supplied to the steam generator; and
a water supply hose guiding water from the reservoir to the steam generator.
18. The dryer of claim 17, wherein the reservoir is configured as a cartridge detachably installed at a drawer which is installed at a front upper portion of the main body such that it can be drawn out.
19. The dryer of claim 17, further comprising:
a pump or a valve for opening and shutting the water supply hose.
20. The dryer of claim 8, wherein the steam generator is formed of an aluminum pipe or a copper pipe.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A rotorcraft comprising:
a fuselage;
a mast having proximal and distal ends, the mast protruding outwardly from an upper surface of the fuselage;
a mast flange pivotally mounted to the fuselage by a pivot, the mast being affixed to the mast flange;
mast tilt actuator coupled to the fuselage and mast flange and operable to adjust an orientation of the flange;
a rotor hub rotationally mounted to the mast proximate the distal end;
a plurality of rotor blades, each having a proximal end rotatably mounted to the hub and having a pitch control arm secured proximate the proximal end thereof;
a swashplate encircling the mast and having a rotating plate and a non-rotating plate, the rotating plate being rotatably mounted to the non-rotating plate;
a plurality of pitch control rods coupling the pitch control arms to the rotating plate;
a plurality of swashplate actuators rigidly mounted to the mast flange and coupled to the non-rotating plate, the swashplate actuators selectively activated to change an orientation of the non-rotating plate.
2. The rotorcraft of claim 1, wherein the mast flange is rigidly mounted to the mast proximate the proximal end thereof;
wherein the plurality of swashplate actuators are rigidly mounted to the mast flange.
3. The rotorcraft of claim 2, wherein the mast flange is monolithically secured to the mast.
4. The rotorcraft of claim 2, further comprising:
a shroud surrounding at least a portion of the mast and defining a mast fluid path between the shroud and mast, a lower edge of the shroud interfacing with the mast flange to form a seal operable to resist airflow therethrough; and
a plenum in fluid communication with the fluid path.
5. The rotorcraft of claim 4, wherein an upper edge of the shroud is configured to complete at least one of encircling a portion of the rotor hub and being encircled by the rotor hub.
6. The rotorcraft of claim 5, further comprising a rotary seal operable to restrict airflow between the rotor hub and shroud.
7. The rotorcraft of claim 6, wherein the rotary seal comprises a flexible skirt secured to an inner surface of one of the rotor hub and shroud.
8. The rotorcraft of claim 4, wherein each blade of the plurality of blades comprises a blade duct extending along at least a portion of the length thereof; and
wherein the rotor hub defines a rotor cavity in fluid communication with the blade ducts of the each blade and the mast fluid channel.
9. The rotorcraft of claim 8, wherein each blade of the plurality of blades comprises a blade spar and the rotor hub comprises a plurality of blade spar apertures, the blade spar of each blade extending into a respective blade spar aperture of the plurality of blade spar apertures;
wherein the pitch control arms are secured to the blade spars and are positioned within the rotor cavity.
10. The rotorcraft of claim 9, wherein the blade ducts comprise hollow portions of the blade spars.
11. The rotorcraft of claim 10, further comprising blade duct fairings, each blade duct fairing positioned within the rotor cavity around a distal edge of one of the blade ducts and having a contour effective to reduce pressure losses of air flowing from the rotor cavity into a corresponding blade duct of the blade ducts.
12. The rotorcraft of claim 4, wherein the plenum has an orientation with respect to the shroud effective to cause rotational flow around the mast of air forced into the mast fluid path from the plenum.
13. The rotorcraft of claim 4, further comprising a mast fairing secured to the rotor hub and encircling the mast along a portion thereof between the proximal and distal ends thereof, the mast fairing having a contour effective to reduce pressure losses of air flowing from the mast fluid path into the rotor cavity.
14. The rotorcraft of claim 4, further comprising a compressed air source in fluid communication with the plenum.
15. The rotorcraft of claim 14, wherein the compressed air source is a bypass turbine of a jet engine.
16. The rotorcraft of claim 15, wherein:
each blade of the plurality of blades has a length and comprises a blade duct extending along at least a portion of the length;
the rotor hub defines the rotor cavity in fluid communication with the blade duct corresponding to each blade of the plurality of blades and the mast fluid channel; and
a tip jet is secured to each blade and in fluid communication with the blade duct corresponding thereto.
17. The rotorcraft of claim 1, wherein the mast tilt actuator and pivot are mounted to the fuselage by at least one vibration suppression component.
18. The rotorcraft of claim 1, further comprising:
an airframe having the mast mounted thereto, the airframe having a control system housed therein and coupled to the swashplate actuators, the control system being programmed to activate the swashplate actuators in response to at least one of flight conditions and pilot inputs effective to change at least one of a collective pitch and a cyclic pitch of the blades.
19. The rotorcraft of claim 18, further comprising, a mast tilt actuator coupled between the mast and the airframe;
wherein the control system is programmed to activate the mast tilt actuator in response to at least one of flight conditions and pilot inputs.