The present invention relates to systems and methods for generating electrical power onboard an aircraft, such as a helicopter.
Providing electrical power onboard a helicopter, particularly to helicopter rotor blades for deicing, has traditionally required the use of gearbox mounted generators, located remotely from the rotor blades, which transmit electrical power to the rotor blades through slip rings, as shown in
Responsive to the foregoing challenges, Applicant has developed an innovative onboard aircraft electrical generator comprising: a rotary outer housing having a central elongated axis and adapted to drive an aircraft blade assembly, said outer housing having an upper end proximal to the aircraft blade assembly, a lower end distal from the aircraft blade assembly, and a varied cross-sectional thickness at points along the elongated axis; a stator assembly disposed within the outer housing, said stator assembly including an armature element or a field element, and having associated electrical terminals; and a rotor assembly disposed within the stator assembly, said rotor assembly including a field element or an armature element.
Applicant has further developed an innovative onboard aircraft electrical generator comprising: a rotary outer housing adapted to drive an aircraft blade assembly, said outer housing having an elongated axis, an upper end proximal to the aircraft blade assembly, and a lower end distal from the aircraft blade assembly; a stator assembly disposed within the outer housing, said stator assembly including an armature element or a field element, and having associated electrical terminals; and a rotor assembly disposed within the stator assembly, said rotor assembly including a field element or an armature element; and a cooling housing contacting the upper end of the elongated outer housing.
Applicant has still further developed an innovative onboard aircraft electrical generator comprising: a rotary outer housing having a central elongated axis and adapted to drive an aircraft blade assembly, said outer housing having an upper end proximal to the aircraft blade assembly, and a lower end distal from the aircraft blade assembly; a stator assembly disposed within and fastened to the outer housing, said stator assembly including an armature element or a field element, wherein said stator assembly extends more than half of a distance between the outer housing upper end and lower end measured along the central elongated axis; and a rotor assembly disposed within the stator assembly relative to the central elongated axis, said rotor assembly including a field element or an armature element.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only, and are not restrictive of the invention as claimed.
In order to assist the understanding of this invention, reference will now be made to the appended drawings, in which like reference numerals refer to like elements. The drawings are exemplary only, and should not be construed as limiting the invention.
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. With reference to
With continued reference to
With reference to
The electrical generating components of the generator 100 may include a stator assembly 102 disposed within the elongated outer housing 103. The stator assembly 102 may comprise one or more stator elements disposed concentrically about the main rotary shaft 101 between an upper bearing assembly 107 and a lower bearing assembly 108. The upper and lower bearing assemblies 107 and 108 may permit the stator assembly 102 to be rotated with the outer housing 103. Preferably the stator assembly 102 may be rotated by the rotor gearbox 210 at the same rotational speed as the outer housing 103, and thus at the same rotational speed as the rotor blades 120. The synchronous rotation of the stator assembly 102 and the rotor blades 120 may facilitate the electrical connection of the generator 100 (through the stator assembly 102) to the rotor blade heating elements without the need for slip rings.
The rotor assembly 104 may be disposed between the stator assembly 102 and the main shaft 101. The rotor assembly 104 may comprise one or more field elements, provided by a permanent magnet or field winding, disposed concentrically about the main shaft 101. Thus, it is appreciated that the generator 100 may be implemented as a homopolar generator or as a wound field generator without departing from the intended scope of the present invention. A separate, optional, driving mechanism may rotate the inner rotor assembly 104 counter to the rotation direction of the stator assembly 102, which may enhance the effect (electricity generation) from rotation.
For example, in a non-limiting embodiment, a 20 kW-capable generator may have a diameter of approximately 3.7 inches and an axial length of approximately 18 inches. For such high aspect ratio generators, a permanent magnet rotor assembly 104 may be relatively easy to manufacture, however, the stator assembly 102 armature may be difficult to wind. Therefore, a split stator assembly 102 configuration may be provided that features two or more stators vertically stacked and connected either in series or in parallel, as shown in
With continued reference to
With reference to
Maintaining an acceptable temperature profile for the generator 100 may require special design of the main mast 110 and inclusion of the cooling dome 106. Heat generated as a result of the operation of the generator 100 may be extracted by conduction through the main mast 110 outer housing 103, which is preferably aluminum, to the cooling dome or housing 106, which is also preferably aluminum, mounted on top of the main mast. The length of the generator 100, as compared with its diameter, may cause one end to attain a substantially different temperature than the other while in operation. This is exemplified by thermal analysis, the results of which are depicted in
Due to the fact that differential temperature of the generator 100 along its axis may cause differential thermal expansion issues, different outer housing 103 wall thickness tapers may be used to control the temperature variation along such axis. For example, by implementing a draft angle of 1.5° of increasing wall thickness along part or all of the length of the outer housing 103, the temperatures along the axis of the generator 100 may be substantially evened.
Because the generator 100 is cooled by conduction through the outer housing 103 to the cooling dome or housing 106, the inclusion and location of the rectifiers 105 may pose a challenging problem which may be solved by using modular rectifier bridges whose thermal coefficient (Junction to Base) is known and well-managed.
It will be apparent to those skilled in the art that variations and modifications of the present invention can be made without departing from the scope or spirit of the invention. For example, the end use of the power generated by the described generator need not be limited to deicing applications. Further, it should be appreciated that the variation of the cross-sectional wall thickness of the outer housing may be varied itself without departing from the intended scope of the present invention so long as such variation provides temperature management, as expressed above. Thus, it is intended that the present invention cover all such modifications and variations of the invention, provided they come within the scope of the appended claims and their equivalents.
This application relates to, and claims the benefit of the earlier filing date and priority of U.S. Provisional Patent Application No. 61/813,619, filed on Apr. 18, 2013, entitled “Mast-Mounted Generator With Counter-Rotating Stator.”
Number | Name | Date | Kind |
---|---|---|---|
3997131 | Kling | Dec 1976 | A |
4472649 | Namba | Sep 1984 | A |
5864189 | Tadao et al. | Jan 1999 | A |
6769874 | Arel | Aug 2004 | B2 |
7750521 | Qu | Jul 2010 | B2 |
8464511 | Ribarov | Jun 2013 | B1 |
8841584 | Bulin | Sep 2014 | B2 |
20030102749 | Kuch et al. | Jun 2003 | A1 |
20050242233 | Battisti | Nov 2005 | A1 |
20070138897 | Asaba | Jun 2007 | A1 |
20090289516 | Hopewell | Nov 2009 | A1 |
20100127496 | Burkholder | May 2010 | A1 |
20110024567 | Blackwelder | Feb 2011 | A1 |
20110025067 | Cipriani | Feb 2011 | A1 |
20110259996 | Vetters | Oct 2011 | A1 |
20110290942 | Imbert | Dec 2011 | A1 |
Number | Date | Country |
---|---|---|
2390989 | Nov 2011 | EP |
2528203 | Nov 2012 | EP |
Number | Date | Country | |
---|---|---|---|
20140312722 A1 | Oct 2014 | US |
Number | Date | Country | |
---|---|---|---|
61813619 | Apr 2013 | US |