Adjusting apparatus for adjusting the pitch angle of propeller blades, variable-pitch propeller, control function which can be implemented in a computer, and method for adjusting the pitch angle of propeller blades
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/00
B64C-011/06
B64C-011/30
B63H-001/06
F01D-007/00
F03B-003/14
F04D-029/36
출원번호
US-0306429
(2007-06-25)
등록번호
US-8109728
(2012-02-07)
우선권정보
DE-10 2006 029 057 (2006-06-24)
국제출원번호
PCT/IB2007/052451
(2007-06-25)
§371/§102 date
20090204
(20090204)
국제공개번호
WO2008/001299
(2008-01-03)
발명자
/ 주소
Neitzke, Klaus-Peter
Ulrich, Andreas
출원인 / 주소
Airbus Deutschland GmbH
대리인 / 주소
Greenblum & Bernstein, P.L.C.
인용정보
피인용 횟수 :
2인용 특허 :
1
초록▼
Apparatus for adjusting pitch angle of propeller blades of a variable-pitch propeller. The blades being adjustable in a first blade pitch-angle range with positive pitch angles, in a second blade pitch-angle range, and in a third blade pitch-angle range with negative pitch angles. The second blade p
Apparatus for adjusting pitch angle of propeller blades of a variable-pitch propeller. The blades being adjustable in a first blade pitch-angle range with positive pitch angles, in a second blade pitch-angle range, and in a third blade pitch-angle range with negative pitch angles. The second blade pitch-angle range is an intermediate range located between the first and the third blade pitch-angle range, which includes the pitch-angle range where blade drag is a minimum, and ranges of positive pitch angles with low thrust and of negative pitch angles with low reverse thrust. The apparatus provides adjustment of the propeller blades from the first to the third blade pitch-angle range and vice versa, and is designed to be operated so that at least a first group of propeller blades can be rotated through the second blade pitch-angle range, while propeller blades in another group are in a positive blade pitch-angle range.
대표청구항▼
1. An adjusting apparatus (9) for adjusting the pitch angle of propeller blades (1, 2, 3, 4, 5, 6, 7, 8) of a variable-pitch propeller in a first blade pitch-angle range with positive pitch angles at which the propeller blades (10) produce thrust, in a second blade pitch-angle range, in a third blad
1. An adjusting apparatus (9) for adjusting the pitch angle of propeller blades (1, 2, 3, 4, 5, 6, 7, 8) of a variable-pitch propeller in a first blade pitch-angle range with positive pitch angles at which the propeller blades (10) produce thrust, in a second blade pitch-angle range, in a third blade pitch-angle range with negative pitch angles, at which the propeller blades produce reverse thrust with the propeller rotating in the same direction, with the second blade pitch-angle range being a pitch-angle intermediate range located between the first and the second blade pitch-angle range, which includes the pitch-angle range in which the blade drag is a minimum, as well as a range of positive pitch angles with low thrust and a range of negative pitch angles with low reverse thrust, and with the adjusting apparatus being able to provide adjustment of the propeller blades (1, 2, . . . ) from the first to the third blade pitch-angle range and vice versa, characterized in that the adjusting apparatus (9) is designed such that, on the basis of it being operated by means of an operating apparatus, at least a first group (A) of the propeller blades (1, 2, . . . ) can be rotated through the second blade pitch-angle range, while the propeller blades in another group (B) are in a positive blade pitch-angle range. 2. The adjusting apparatus as claimed in claim 1, characterized in that the adjusting apparatus (9) is designed such that only the first group (B) of propeller blades can be rotated through the second pitch-angle range to the third blade pitch-angle range in order to produce reverse thrust, with the reverse thrust which is produced by the propeller blades (B) which have been rotated through the blade pitch-angle range of critical pitch angles being greater than the thrust produced by the propeller blades in the first group (A) when the variable-pitch propeller is in the reverse-thrust position. 3. The adjusting apparatus (9) as claimed in claim 1, characterized in that the adjusting apparatus (9) is designed such that at least two groups (A, B) of propeller blades can each be rotated with a time offset with respect to one another from the first blade pitch-angle range through the second blade pitch-angle range to the third blade pitch-angle range, with the time offset being set such that a propeller blade setting can be provided at which the propeller blades in the one group (B) are located in the first or the third blade pitch-angle range, while the propeller blades in the other group (A) are located in the second blade pitch-angle range, and vice versa. 4. The adjusting apparatus (9) as claimed in claim 1, characterized in that the adjusting apparatus has drive apparatuses for adjusting the pitch angle of in each case one propeller blade, which drive apparatuses are connected via signal or data lines to the operating apparatus for commanding the drive apparatus and for adjusting the propeller blades. 5. The adjusting apparatus (9) as claimed in claim 1, characterized in that the adjusting apparatus (9) has at least one adjusting element (94) which can be adjusted by means of an operating apparatus and at least one intermediate element (91, 92) for adjusting in each case one propeller blade (1, 2, . . . ), which is in each case hinged on the one hand on the adjusting element (94) and on the other hand on a connecting apparatus (95) of the respective propeller blade (1, 2, . . . ), with the geometric arrangement comprising the at least one adjusting element, the at least one intermediate element and the connecting apparatus (95, 195, 295) resulting in a transfer function of the blade pitch adjustment as a function of the adjustment of the adjusting element, for which: in a first adjustment range of the at least one adjusting element, the pitch angles of the various groups of propeller blades are in the first blade pitch-angle range and differ by a maximum amount of 10 degrees, in a second adjustment range of the at least one adjusting element, the pitch angles of a first group of propeller blades are in the second blade pitch-angle range and the pitch angles of the further groups (B) of propeller blades are in the first blade pitch-angle range, in a third adjustment range of the at least one adjusting element, in order to implement a reverse-thrust operating mode, the pitch angles of the first group of propeller blades are in the third blade pitch-angle range, and the pitch angles of the further groups (B) of propeller blades are in the first blade pitch-angle range. 6. The adjusting apparatus (9) as claimed in claim 5, characterized in that a crank (92, 192, 292) is fitted in a rotationally fixed form to each propeller blade, on which crank (92, 192, 292) in each case one connecting apparatus (95, 195, 295) is provided for hinged holding of an intermediate element, with the connecting apparatus (95, 195, 295) being located eccentrically with respect to the propeller axis, the at least one intermediate element (91, 191, 291) for adjusting in each case one propeller blade (1, 2, . . . ), which is in each case hinged on the one hand on the adjusting element (94) and on the other hand on the connecting apparatus (95, 195, 295), the adjusting apparatus (9) has one or more adjusting elements for coupling the output of the operating apparatus and the intermediate elements. 7. The adjusting apparatus (9) as claimed in claim 5, characterized in that each adjusting element is guided such that it can be moved by means of a guide apparatus which runs along the propeller axis (X), with the rotation angle of the adjusting element being constant while it is being moved, in which case one guide apparatus can be provided for in each case one adjusting element and/or one guide apparatus can be provided for a plurality of adjusting elements. 8. The adjusting apparatus (9) as claimed in claim 7, characterized in that the adjusting elements are arranged on the same guide apparatus, or in that a plurality of guide apparatuses are provided, with each adjusting element which is associated with one group of propeller blades being arranged on a dedicated guide apparatus. 9. The adjusting apparatus (9) as claimed in claim 5, characterized in that the adjusting apparatus (9) has at least one spindle which runs in the longitudinal direction of the propeller axis (X), and on which the adjusting element (94, 194) can be moved with the rotation angle being varied, in which case one spindle can be provided for in which case one adjusting element, and/or one spindle can be provided for a plurality of adjusting elements. 10. The adjusting apparatus (9) as claimed in claim 5, characterized in that in each case one adjusting element (194, 294) is provided for each group of propeller blades. 11. The adjusting apparatus (9) as claimed in claim 10, characterized in that the adjusting elements are arranged on the same spindle or in that a plurality of spindles are provided, with each adjusting element which is associated with one group of propeller blades being arranged on a dedicated spindle. 12. The adjusting apparatus (9) as claimed in claim 10, characterized in that the adjusting elements (194, 294) for different groups of propeller blades are mechanically coupled, with the connecting apparatuses (95) on the blade roots (93) of the first group (A) of propeller blades in each case being offset with respect to one another seen in the rotation direction about the propeller axes with respect to the connecting apparatuses (95) on the blade roots (93) of the at least one further group (B). 13. The adjusting apparatus (9) as claimed in claim 1, characterized in that each adjusting element (194, 294) adjusts one group of propeller blades, and in that each adjusting element is operated independently by means of an operating apparatus and a drive apparatus. 14. The adjusting apparatus (9) as claimed in claim 5, characterized in that the adjusting apparatus has an adjusting element (294) which can be adjusted by means of the operating apparatus and which can be rotated about the propeller axis (X), as well as in each case one intermediate element which is hinged on the adjusting element and the respective connecting apparatus of the respective propeller blade. 15. The adjusting apparatus (9) as claimed in claim 14, characterized in that the adjusting apparatus (9) has a spindle which runs in the longitudinal direction of the propeller axis (X) and on which the adjusting element (94, 194) can be moved with the rotation angle being varied. 16. The adjusting apparatus (9) as claimed in claim 14, characterized in that each adjusting element is guided such that it can be moved by means of a guide apparatus which runs along the propeller axis (X), with the rotation angle of the adjusting element while it is being moved being constant, in which case one guide apparatus can be provided for in each case one adjusting element, and/or one guide apparatus can be provided for a plurality of adjusting elements. 17. The adjusting apparatus (9) as claimed in claim 1, characterized in that the adjusting apparatus is intended for coupling to an even number of blade roots (93), with the propeller blades in the first group (A) of propeller blades being arranged alternately with the propeller blades in the second group (B) of propeller blades, seen in the rotation direction about the propeller axis (X). 18. The adjusting apparatus (9) as claimed in claim 1, characterized in that the adjusting apparatus is intended for coupling to a total of four propeller blades, of which two propeller blades which are opposite with respect to the propeller axis (X) are allocated to the first group of propeller blades. 19. The adjusting apparatus (9) as claimed in claim 1, characterized in that the adjusting apparatus is coupled to a total of six or eight propeller blades, of which a total of two propeller blades which are opposite with respect to the propeller axis (X) are allocated to the first group of propeller blades. 20. The adjusting apparatus (9) as claimed in claim 1, characterized in that the adjusting apparatus is coupled to a total of nine propeller blades, of which a total of three propeller blades which are located in this way are allocated to the first group of propeller blades, in that two propeller blades for the second group of propeller blades are located between two adjacent propeller blades (95) in the first group of propeller blades, seen in the rotation direction about the propeller axis (X). 21. The adjusting apparatus (9) as claimed in claim 1, characterized in that a plurality of first groups (A) of propeller blades are provided. 22. A variable-pitch propeller with an adjusting apparatus as claimed in claim 6, with the variable-pitch propeller having a propeller axis and a plurality of blade roots, which are fitted thereto along its circumferential direction and each have a bearing device for bearing in each case one propeller blade, in which case one propeller blade (1, 2, . . . ) is mounted in the respective bearing device such that it can rotate about a blade axis (Y) which extends at an angle, and in particular radially, with respect to the propeller axis (X). 23. The variable-pitch propeller with an adjusting apparatus (9) as claimed in claim 22, characterized in that an even number of blade roots (93) with force action points (95) are provided, with the force action points (95) of the blade roots (93) of the first group (A) of propeller blades being arranged alternately with the blade roots (93) of the second group (A) of propeller blades, seen in the rotation direction about the propeller axis (X). 24. The variable-pitch propeller with an adjusting apparatus (9) as claimed in claim 22, characterized in that a total of four force action points (95) are provided and are arranged on in each case one blade root (93), of which two force action points (95) which are opposite with respect to the propeller axis (X) are allocated to the first group of propeller blades. 25. The variable-pitch propeller with an adjusting apparatus (9) as claimed in claim 22, characterized in that a total of six or eight force action points (95) are provided and are arranged on in each case one blade root (93), of which a total of two force action points (95) which are located opposite with respect to the propeller axis (X) are allocated to the first group of propeller blades. 26. The variable-pitch propeller with an adjusting apparatus (9) as claimed in claim 22, characterized in that a total of nine force action points (95) are provided and are arranged on in each case one blade root (93), of which a total of three force action points (95) which are located in this way are allocated to the first group of propeller blades, in that two force action points (95) for the second group of propeller blades are located between two adjacent force action points (95) for the first group of propeller blades, seen in the rotation direction about the propeller axis (X). 27. A control apparatus for actuating an adjusting apparatus as claimed in claim 1, in order to adjust the blade pitch angle of propeller blades by adjustment of the adjusting apparatus. 28. A control function which can be implemented in a computer for adjustment of an adjusting apparatus for propellers, with the control program using data for adjusting propeller blades of the propeller as an input variable and, as an output, producing command variables for operating the adjusting apparatus as claimed in claim 1. 29. A method for adjusting the pitch angle of propeller blades (1, 2, 3, 4, 5, 6, 7, 8) of a variable-pitch propeller in a first blade pitch-angle range with positive pitch angles at which the propeller blades (10) produce thrust, in a second blade pitch-angle range, in a third blade pitch-angle range with negative pitch angles, at which the propeller blades produce reverse thrust with the propeller rotating in the same direction, with the second blade pitch-angle range being a pitch-angle intermediate range located between the first and the second blade pitch-angle range, which includes the pitch-angle range in which the blade drag is a minimum, as well as a range of positive pitch angles with low thrust and a range of negative pitch angles with low reverse thrust, characterized in that the method provides a cruise-flight operating mode, in which the pitch angles of the various groups of propeller blades are in the first blade pitch-angle range, in that the method provides a reverse-thrust operating mode, in which in a first adjustment range of the at least one adjusting element, the pitch angles of the various groups of propeller blades are in the first blade pitch-angle range, in a second adjustment range of the at least one adjusting element, the pitch angles of a first group of propeller blades are in the second blade pitch-angle range of critical pitch angles and the pitch angles of the further groups (B) of propeller blades are in the first blade pitch-angle range, in a third adjustment range of the at least one adjusting element, in order to provide a reverse-thrust operating mode, the pitch angles of the first group of propeller blades are in the third blade pitch-angle range and the pitch angles of the further groups (B) of propeller blades are in the first blade pitch-angle range. 30. The method for adjusting the pitch angle of propeller blades (1, 2, 3, 4, 5, 6, 7, 8) of a variable-pitch propeller as claimed in claim 29, characterized in that, in the reverse-thrust operating mode, only the propeller blades in the at least one group (B) can be rotated through the second range of critical pitch angles to the third pitch-angle range, in which case, when the variable-pitch propeller is in the reverse-thrust position, the reverse thrust which is produced by those propeller blades (B) which have been rotated through the range of critical pitch angles is greater than the thrust which is produced by the other propeller blades (A). 31. The method for adjusting the pitch angle of propeller blades (1, 2, 3, 4, 5, 6, 7, 8) of a variable-pitch propeller as claimed in claim 29, characterized in that, in the reverse-thrust operating mode, at least two groups (A, B) of propeller blades are each rotated with a time offset with respect to one another from the first adjustment range through the second range of critical pitch angles to the third range, such that a propeller-blade setting can be provided for which the propeller blades of the one group (B) are located in the first or third pitch-angle range, while the propeller blades of the other group (A) are located in the second range of critical pitch angles, and vice versa.
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이 특허에 인용된 특허 (1)
Sum Michael J. (Cincinnati OH) Bennett George W. (Cincinnati OH) Merrell Steven A. (Cincinnati OH) Walker Neil (Cincinnati OH), Aircraft propeller speed control.
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