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公开(公告)号：US4891935A
公开(公告)日：1990-01-09
申请号：US357698
申请日：1989-05-26
申请人： Leroy D. McLaurin , David Y. K. Toy
发明人： Leroy D. McLaurin , David Y. K. Toy
CPC分类号： F23D11/007 , F23D11/24 , F23D2211/00
摘要： A fuel nozzle assembly having a fuel nozzle tip at one end of a fuel delivery tube and a supporting flange at the other end. An air delivery tube, also secured to the support flange, encloses the fuel delivery tube to define an annular air passage therebetween. An integral fuel nozzle/end cap engages the fuel and air tubes and provides passages for fuel flowing from the fuel delivery tube and air flowing from the air delivery tube. Biasing means exerts an axial force on the air delivery tube to tighten the engagement of the tubes into an air-tight fit.
摘要翻译： 一种燃料喷嘴组件，其具有在燃料输送管的一端处的燃料喷嘴尖端和另一端的支撑凸缘。 也固定到支撑凸缘的空气输送管封闭燃料输送管以在其间限定环形空气通道。 一体的燃料喷嘴/端帽与燃料和空气管接合，并为从燃料输送管流出的燃料和从空气输送管流出的空气提供燃料通道。 偏压装置在空气输送管上施加轴向力，以将管接合成气密配合。
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公开(公告)号：US5639216A
公开(公告)日：1997-06-17
申请号：US606909
申请日：1996-02-26
CPC分类号： F01D5/187 , F05D2240/81
摘要： A turbine blade has a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Two cooling air passages are formed in the blade root platform just below its upper surface. Each passage extends radially outward from an inlet that receives a flow of cooling air and then extend axially along almost the entire length of the platform. Each passage also has an outlet formed in the downstream face of the platform that allows the cooling air to exit the platform and enter the hot gas flow path. The passages are formed in portions of the platform that overhang the shank portion of root.
摘要翻译： 涡轮机叶片具有专门用于冷却叶片根部的平台部分的冷却空气流动路径。 两个冷却空气通道形成在其上表面正下方的叶片根平台中。 每个通道从容纳冷却空气流的入口径向向外延伸，然后沿着平台的整个长度轴向延伸。 每个通道还具有形成在平台的下游面中的出口，其允许冷却空气离开平台并进入热气流动路径。 通道形成在平台的突出在根部的柄部上的部分中。
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公开(公告)号：US4648799A
公开(公告)日：1987-03-10
申请号：US647859
申请日：1984-09-05
申请人： David L. Brown , Leroy D. McLaurin
发明人： David L. Brown , Leroy D. McLaurin
CPC分类号： F01D5/187 , F01D5/3015
摘要： The invention comprises a retrofit turbine blade cooling apparatus for replacing non-cooled turbine blades in presently existing combustion turbines. The cooling apparatus comprises a turbine blade structured for fluid cooling and a sealing apparatus structured to cooperate with a root portion of the turbine blade and a subadjacent portion of a turbine disc to force cooling fluid into the turbine blade. Use of the cooling apparatus requires no modification or disassembly of the rotor assembly.
摘要翻译： 本发明包括一种用于更换现有燃烧涡轮机中的非冷却涡轮叶片的改型涡轮叶片冷却装置。 冷却装置包括构造成用于流体冷却的涡轮叶片和被构造成与涡轮叶片的根部配合的密封装置和涡轮盘的下部，以迫使冷却流体进入涡轮叶片。 使用冷却装置不需要改装或拆卸转子组件。
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公开(公告)号：US4915587A
公开(公告)日：1990-04-10
申请号：US261668
申请日：1988-10-24
CPC分类号： F01D5/326
摘要： An apparatus and method is provided for locking side entry blades, in a rotor, such as used in compressors, turbines and fans. The apparatus utilizes arcuate locking devices retained in a circumferential groove in the periphery of the rotor. Each locking device features a key which engages a keyway in the side of the blade root shank. Use of the locking devices does not require that the blades having abutting platforms.
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5.发明授权Method and apparatus for vane segment support and alignment in combustion turbines 失效燃气轮机叶片段支撑和对准的方法和装置
公开(公告)号：US4890978A
公开(公告)日：1990-01-02
申请号：US259811
申请日：1988-10-19
CPC分类号： F01D9/04 , F01D25/246 , F05D2230/644
摘要： Methods and apparatus for vane segment alignment and support in a combustion turbine. The vane segment alignment device is comprised of a rotatable, eccentric bushing and pin which is inserted into a slot of the vane segment. The eccentric bushing is further comprised of a cover plate which is peened to a splined torque plate thus holding the eccentric bushing in place against the vane segment but allowing for fine adjustments of the alignment of the vane segments. The vane segment support and alignment device provides for efficient and economical adjustment of the vane segments especially in electric generating plants where combustion turbines undergo high peak load operation. Additionally, the vane segment support and alignment device transfers torques and moments generated by aerodynamic flow from the vane segments to an inner cylinder thereby reducing the amount of misalignment due to aerodynamic drag.
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