초록 ▼

The bleed valve actuating system is for use in a gas turbine engine. The system comprises an actuator mounted adjacent the engine case and having a main actuation axis extending generally parallel to a surface of the engine case. A drive rod extends from the bleed valve to the actuator generally per

The bleed valve actuating system is for use in a gas turbine engine. The system comprises an actuator mounted adjacent the engine case and having a main actuation axis extending generally parallel to a surface of the engine case. A drive rod extends from the bleed valve to the actuator generally perpendicularly with reference to the main actuation axis of the actuator. The drive rod connected to the actuator via a linkage mechanically connects the actuator to the drive rod. The linkage is configured to convert axial motion of the actuator along the main actuation axis into generally perpendicular motion of the drive rod.

대표청구항 ▼

What is claimed is: 1. A gas turbine engine, the engine comprising a case surrounding a compressor bleed valve, with the compressor bleed valve being inside the case, the engine having a bleed valve actuating system including an actuator mounted outside of and adjacent to the engine case and having

What is claimed is: 1. A gas turbine engine, the engine comprising a case surrounding a compressor bleed valve, with the compressor bleed valve being inside the case, the engine having a bleed valve actuating system including an actuator mounted outside of and adjacent to the engine case and having a main actuation axis extending generally parallel to a surface of the engine case, a drive rod extending from the bleed valve through the engine case to the actuator generally perpendicularly with reference to the main actuation axis of the actuator, the drive rod connected to the actuator via a linkage mechanically connecting the actuator to the drive rod, the linkage configured to convert axial motion of the actuator along the main actuation axis into generally perpendicular motion of the drive rod. 2. The gas turbine engine as defined in claim 1, wherein the linkage comprises a member pivotally connected to the engine case. 3. The gas turbine engine as defined in claim 2, wherein the member is pivotally connected to the engine case through a bracket connected to the actuator. 4. The gas turbine engine as defined in claim 1, wherein the main actuation axis of the actuator is substantially parallel to a main shaft axis of the engine. 5. The gas turbine engine as defined in claim 1, wherein the main actuation axis of the actuator is aligned generally circumferentially relative to the engine. 6. The gas turbine engine as defined in claim 1, wherein the drive rod is substantially radially aligned relative to the engine. 7. The gas turbine engine as defined in claim 1, wherein the actuator is pivotally bolted to the linkage. 8. The gas turbine engine as defined in claim 1, wherein the actuator comprises a rod and cylinder, the rod pivotally connecting to the linkage. 9. The gas turbine engine as defined in claim 1, wherein the linkage comprises a bell crank pivotally mounted to the engine. 10. The gas turbine engine as defined in claim 9, wherein the linkage further comprises a lever pivotally connecting the bell crank to the actuator. 11. A bleed valve actuating system for a gas turbine engine, the system comprising: a rod partially extending inside a case of the engine and connected to a bleed valve inside the case of the engine, the rod having an end projecting generally radially out of the engine case; a linear actuator having a fixed portion and a movable portion, the fixed portion being rigidly connected to a fixed structure of the engine, the actuator extending generally parallel to a surface of the engine case; a lever having opposite first and second ends, the first end of the lever being pivotally connected to the movable portion of the actuator and defining a first pivot axis; a bell crank having opposite first and second ends and a pivot point, the ends and the pivot point arranged relative to one another to define a triangle therebetween, the pivot point being pivotally connected to the fixed structure and defining a second pivot axis, the first end of the bell crank being pivotally connected to the second end of the lever and defining a third pivot axis, the second end of the bell crank being pivotally connected to the free end of the rod and defining a fourth pivot axis; wherein the first, second, third and fourth pivot axes are parallel, and wherein the linkage is configured to convert generally linear axial movement of the actuator into generally linear radial movement of the rod. 12. The system as defined in claim 11, wherein the fixed structure is an external portion of the engine case. 13. The system as defined in claim 11, wherein the pivot point is connected to the external portion of the engine case through a bracket. 14. The system as defined in claim 11, wherein at least one of the connections providing the first and second pivot axes is a bolt and nut assembly configured to permit selective detachment of the actuator from a remainder of the system. 15. A method of servicing a bleed valve of a gas turbine engine, the method comprising: positioning a bleed valve inside an engine case with a bleed valve drive rod passing through the engine case to have an end projecting outside the engine case; providing a bleed valve system having an actuator pivotally connected to the bleed valve drive rod via a pivotal linkage, the linkage configured to convert linear movement of the actuator along the engine case into radial movement of the drive rod radially through the engine case, the linkage mounted to the engine independently of a connection of the linkage to the actuator, the connection of the linkage to the actuator including a releasable pin connection outside the engine case; releasing the releasable pin connection from outside the case; servicing the actuator by removing the actuator from outside the engine case; reconnecting the actuator to the linkage by restoring the releasable pin connection from outside the case. 16. The method as defined in claim 15, wherein the step of servicing the actuator includes replacing the actuator with a replacement actuator. 17. The method as defined in claim 15, further comprising putting the engine back into flight service without re-calibration of the bleed valve.