Precision rotor indexing device
AssigneeGeneral Electric Company
InventorsHugh E. Rosa, Allen A. Slaterpryce
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Abstract
A method and apparatus for providing precisely controlled micro-indexing of rotational elements utilizes a bidirectionally controllable linear force actuator in combination with a self-locking linkage mechanism to frictionally grip and to impart a pure turning moment to the rotational element. The method and apparatus disclosed are especially advantageous for use with large rotational elements, such as the rotors of gas turbines. The indexing method inserts a minimal amount of stored energy into a system thereby virtually eliminating overshoot. In a preferred embodiment comprised of a pair of symmetrical indexing sections, the desired micro-indexing is accomplished while imposing no additional loading on the rotational element.
Claims9
Apparatus for indexing a rotor member of the type having a cylindrical surface, comprising:
- a metallic circular band fittable to encircle said cylindrical surface;
- first and second discontinuities spaced 180 degrees apart in said circular band;
- first and second attachment points at extremities of said circular band at said first discontinuity;
- third and fourth attachment points at extremities of said circular band at said second discontinuity;
- a first self-locking compound linkage assembly joining said first and second attachment points;
- a second self-locking compound linkage assembly joining said third and fourth attachment points;
- said first self-locking compound linkage assembly including first means for locking said circular band to said rotor member in response to a first force applied in a first tangential direction to said first self-locking compound linkage assembly and for releasing said circular band in response to a second force applied thereto in a second tangential direction;
- said second self-locking compound linkage assembly including second means for locking said circular band to said rotor member in response to said first force applied in said first tangential direction to said second self-locking compound linkage assembly and for releasing said circular band in response to said second force applied thereto in said second tangential direction;
- a first linear actuator effective to apply a selected one of said first and second forces to said first self-locking compound linkage assembly;
- a second linear actuator effective to apply a same one of said first and second forces to said second self-locking compound linkage assembly whereby said cylindrical surface receives substantially equal tangential forces spaced 180 degrees apart for imparting pure rotating moment to said rotor member;
- each said self-locking compound linkage assembly comprising two links pivotally secured to each other, a first one of said links being pivotally secured to one of said first or third attachment points and a second of said links being pivotally secured to one of said second or fourth attachment points, each of said linear actuators being pivotally secured to a respective one of said links;
- and
- said first and second linear actuators being further effective, when said first force is applied to said first and second self-locking compound linkage assemblies thereby locking said circular band to said cylindrical surface, to continue substantially linear motion whereby a controlled unidirectional rotation of said rotor member is produced.
A method of precisely indexing a gas turbine rotor having a rotational element with a circular outer surface rigidly coupled in torsion to said rotor and a circular band having at least first and second circumferential discontinuities spaced 180 degrees apart therein around said circular outer surface, said method comprising the steps of:
- (a) selectively applying frictional and torsional forces to said rotational element at said first and second discontinuities;
- (b) providing first and second compound linkage assemblies, each having a quiescent position, a transitional position and a locked position at said first and second discontinuities, to flexibly retain said circular band and to controllably adjust a circumferential spacing at said first and second discontinuities in response to an externally applied linear displacement;
- (c) applying first and second linear displacements in a first tangential direction to said first and second compound linkage assemblies to frictionally engage said rotational element as a result of said first and second compound linkage assemblies being moved to their transitional position and to apply a substantially torsional indexing force to said rotational element as a result of said first and second compound linkage assemblies being moved to their locked position and;
- (d) continuing said first and second linear displacements displacement with said first and second compound self-locking linkage assemblies maintained in their locked positions by said displacements whereby a controlled rotation of said gas turbine rotor is attained by a rotational movement of said circular band.
Dependencies are inferred from the claim text.