A turbine combustion chamber is provided with deflectors on the cold side generating vortices in a secondary gas flow into the chamber, thereby confining the flame front under variable operating conditions and cooling the chamber walls. The high-speed cantilever shaft has a longitudinal duct and an
A turbine combustion chamber is provided with deflectors on the cold side generating vortices in a secondary gas flow into the chamber, thereby confining the flame front under variable operating conditions and cooling the chamber walls. The high-speed cantilever shaft has a longitudinal duct and an array of fine orifices in the wall of the shaft for directing pressurized oil jets that impinge on the shaft bearings with little relative speed to increasing wetting of the bearing components. Oil is supplied to the duct by means of a positive-displacement pump directly driven by the output shaft. The pump output pressure is monitored to signal the end of the start-up sequence when the turbine reaches sufficient speed. The turbo-engine further includes devices for decoupling vibrations between the three systems thereof, including a loosely-mounted removable spline pivotable at both ends for coupling the high-speed shaft to the step-down gearbox.
대표청구항▼
I claim: 1. A turbo-engine comprising: a turbine having a high-speed shaft mounted on a first pair of bearing means for delivering rotational mechanical power, a low-speed output shaft for delivering useful rotational mechanical power to a load, a speed step-down mechanism coupling said shafts to o
I claim: 1. A turbo-engine comprising: a turbine having a high-speed shaft mounted on a first pair of bearing means for delivering rotational mechanical power, a low-speed output shaft for delivering useful rotational mechanical power to a load, a speed step-down mechanism coupling said shafts to one another in order to transmit such rotational mechanical power from said high-speed turbine shaft to said low-speed output shaft, said step-down mechanism including a high-speed gearwheel, a shaft for said high-speed gearwheel to rotate thereon and a second pair of bearing means for mounting said high-speed gearwheel on said gearwheel shaft to rotate independently of said turbine high speed shaft, and a spline coupling said high-speed shaft to said high-speed gearwheel of said speed step-down mechanism, wherein said spline is longitudinally traversed by a bore for conveying a mixture of lubricant droplets and air to said high-speed shaft bearings, said droplets assisting in self-balancing said spline and dampening vibrations therein at high shaft speeds. 2. The turbo-engine of claim 1, wherein said bore has a slightly frustoconical shape tapering at an angle of about 1° to the axial direction of said shaft. 3. The turbo-engine of claim 1, wherein said bore has a circumferential cavity about ½ mm deep and in a plane containing the center of gravity said shaft for selfbalancing the shaft spline at high speeds of rotation. 4. A turbo-engine comprising: a turbine having a high-speed shaft for delivering rotational mechanical power, a low-speed output shaft for delivering useful rotational mechanical power to a load, a speed step-down mechanism coupling said shafts to one another in order to transmit such rotational mechanical power from said high-speed turbine shaft to said low-speed output shaft and a spline coupling said speed step-down mechanism to said high-speed shaft; wherein: said spline has first and second longitudinally spaced fluting portions and a length between said fluting portions, said spline comprising a substantially rigid member extending throughout said length, said first fluting portion loosely engaging said high-speed shaft for receiving said rotational mechanical power therefrom, said second fluting portion loosely engaging said speed step-down mechanism for transmitting said rotational mechanical power thereto, whereby said fluting portions of said spline form respective engagements which are rigid in the azimutal direction to transmit rotation from said high-speed shaft to said speed step-down mechanism yet loose in the axial and radial directions and allow said first and second fluting portions of said spline to pivot relative to said turbine high-speed shaft and said speed step-down mechanism respectively to substantially decouple axial and radial vibrations therebetween, compensate thermal expansion and tolerate eccentricity in and misalignments between said high-speed shaft, said spline and said speed step-down mechanism. 5. The turbo-engine of claim 4, wherein said spline includes a pair of opposite ends and said fluting portions are substantially on the opposite ends of said spline. 6. The turbo-engine of claim 5, wherein said loosely engaging fluting portions allow each of said first and second spline ends to respectively pivot about a reduced angle on the turbine high-speed shaft or said speed step-down mechanism. 7. The turbo-engine of claim 4, wherein said spline is a removable spline longitudinally traversed by a bore for conducting a mixture including lubricant droplets. 8. The turbo-engine of claim 7, wherein said bore has a circumferential cavity for self-balancing the spline at high speeds of rotation. 9. The turbo-engine of claim 8, wherein said circumferential cavity is in a plane containing the center of gravity said shaft. 10. The turbo-engine of claim 8, wherein said circumferential cavity is about ½ mm deep. 11. The turbo-engine of claim 7, wherein said spline bore has a slightly frustoconical shape for assisting in conducting said mixture therealong at high shaft speeds. 12. The turbo-engine of claim 7, wherein said mixture comprises a pressurized mixture of oil droplets and air. 13. The turbo-engine of claim 4, wherein said step-down mechanism includes: a high-speed gear wheel coupled to said turbine high-speed shaft and a low- speed gear wheel meshing with said high-speed gear wheel and coupled to said low- speed output shaft; and wherein said high-speed gear wheel has an axial cavity provided with grooves loosely meshing with said second fluting portion of said spline. 14. The turbo-engine of claim 13, further comprising vibration decoupling means interposed between said low-speed gearwheel and said low-speed output shaft for transmitting rotational power therebetween and dampening transmission of azimutal vibrations on said low-speed output shaft. 15. The turbo-engine of claim 13, wherein said turbine high-speed shaft is mounted on a set of bearings and said high-speed gearwheel is mounted on another set of bearings different from said high-speed shaft bearings. 16. A turbo-engine comprising: a turbine having a high-speed shaft for delivering rotational mechanical power, a low-speed output shaft for delivering useful rotational mechanical power to a load, a speed step-down mechanism coupling said shafts to one another in order to transmit such rotational mechanical power from said high-speed turbine shaft to said low-speed output shaft; and a spline coupling said speed step-down mechanism to said high-speed shaft; wherein: said spline has first and second longitudinally spaced fluting portions and a length between said fluting portions, said spline comprising a substantially rigid member extending throughout said length, said first fluting portion loosely engaging said high-speed shaft for receiving said rotational mechanical power therefrom, said second fluting portion loosely engaging said high-speed shaft to said speed step-down mechanism for transmitting said rotational mechanical power thereto, whereby said fluting portions of said spline form respective engagements which are rigid in the azimutal direction to transmit rotation from said high-speed shaft to said speed step-down mechanism yet loose in the axial and radial directions and allow said first and second fluting portions of said spline to pivot relative to said turbine high-speed shaft or said speed step-down mechanism respectively to substantially decouple axial and radial vibrations therebetween, compensate thermal expansion and tolerate eccentricity in and misalignments between said high-speed shaft, said rigid spline member and said speed step-down mechanism; wherein said step-down mechanism includes a high-speed gear wheel coupled to said turbine high-speed shaft and a low-speed gear wheel meshing with said high-speed gear wheel and coupled to said low-speed output shaft; and wherein said high-speed gear wheel has an axial cavity provided with grooves loosely meshing with said second fluting portion of said spline; said turbo-engine further comprising vibration decoupling means interposed between said low-speed gearwheel and said low-speed output shaft for transmitting rotational power therebetween and dampening transmission of azimutal vibrations on said low-speed output shaft, said vibration decoupling means including: a disk secured to the low-speed shaft and having a metal contact surface, and resilient bushing means coupling said metal contact surface of the low-speed gear to said metal contact surface of the low-speed shaft, thereby dampening transmission of vibrations between said metal contact surfaces. 17. The turbo-engine of claim 16, wherein said low-speed gearwheel and said low-speed shaft disk each have facing rigid contact surfaces provided with aligned orifices and rotationally connected by said bushing means, said bushing means comprising bolt means sheathed in resilient material passing through said orifices and resilient washer means between said rigid contact surfaces. 18. The turbo-engine of claim 17, wherein both said rigid contact surfaces are metallic.
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이 특허에 인용된 특허 (15)
Murray Stephen G. (Indianapolis IN), Accessory drive spline lubrication system for a turbine engine reduction gear box.
Clarens, Andres F.; Allaire, Paul E.; Younan, Amir; Wang, Shibo, Gas-expanded lubricants for increased energy efficiency and related method and system.
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