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1. 发明授权

US4427742A Core or core part for use in the lost wax casting process 失效
标题翻译：用于失蜡铸造工艺的芯或芯部件
公开(公告)号：US4427742A
公开(公告)日：1984-01-24
申请号：US316431
申请日：1981-10-29
申请人： Kenneth Willgoose , Rondald Brien , Peter E. Rose , Clifford G. Hannah
发明人： Kenneth Willgoose , Rondald Brien , Peter E. Rose , Clifford G. Hannah
IPC分类号： B22C9/04 , B22C9/10 , B32B9/00
CPC分类号： B22C9/04 , B22C9/10 , Y10T428/268 , Y10T428/30
摘要： A core or core part for use in the lost wax casting process is strengthened by admixture to its material of a proportion of short reinforcing fibres.
摘要翻译：用于失蜡铸造工艺的核心或核心部分通过与其一部分短增强纤维的材料混合而增强。

2. 发明授权

US4688992A Blade platform 失效
标题翻译：刀片平台
公开(公告)号：US4688992A
公开(公告)日：1987-08-25
申请号：US694889
申请日：1985-01-25
申请人： Ralph A. Kirkpatrick , Kenneth Willgoose , Omer D. Erdmann
发明人： Ralph A. Kirkpatrick , Kenneth Willgoose , Omer D. Erdmann
IPC分类号： F01D5/30
CPC分类号： F01D5/3038
摘要： The present invention discloses a turbomachinery blading configuration. The configuration includes a circumferential recess in a blade support structure and a plurality of blades. Each blade has a platform for mounting the blade within the recess. Each platform includes oppositely directed, generally circumferentially facing edges, each edge having a first and second axial surfaces separated by a recess. The surfaces contact matching surfaces on adjacent blades thereby determining predictable load paths for tangential and twisting moment reaction forces acting on the blades.
摘要翻译：本发明公开了一种涡轮机械叶片构造。该构造包括叶片支撑结构中的周向凹部和多个叶片。每个刀片具有用于将刀片安装在凹槽内的平台。每个平台包括相对定向的大致周向的边缘，每个边缘具有由凹部分开的第一和第二轴向表面。表面接触相邻刀片上的匹配表面，从而确定作用在刀片上的切向和扭转力矩反作用力的可预测载荷路径。

3. 发明授权

US5215442A Turbine blade platform damper 失效
标题翻译：涡轮叶片平台阻尼器
公开(公告)号：US5215442A
公开(公告)日：1993-06-01
申请号：US770839
申请日：1991-10-04
申请人： Charles E. Steckle , Philip W. Dietz , Kenneth Willgoose
发明人： Charles E. Steckle , Philip W. Dietz , Kenneth Willgoose
IPC分类号： F01D5/16 , F01D5/22
CPC分类号： F01D5/22 , Y02T50/673 , Y10S416/50 , Y10T29/49337
摘要： A vibration damper for rotor blades of a gas turbine engine has a shaft and a contact head connected thereto. The shaft is slidably inserted in a cylindrical recess incorporated in the rotor blade platform. During rotation of the rotor disk, the shaft of the damping member slides along the shaft axis, whereby the damping member is moved at least in the radial and circumferential directions by centrifugal forces. The contact head of the damping member of one rotor blade finally bears against the platform portion of an adjacent rotor blade, serving to damp vibratory motion of both blades.

4. 发明授权

US4434835A Method of making a blade aerofoil for a gas turbine engine 失效
标题翻译：制造用于燃气涡轮发动机的叶片机翼的方法
公开(公告)号：US4434835A
公开(公告)日：1984-03-06
申请号：US356506
申请日：1982-03-09
申请人： Kenneth Willgoose
发明人： Kenneth Willgoose
IPC分类号： B22C7/02 , B22C9/04 , B22C9/10 , B23P15/04 , F01D5/18 , F01D5/28
CPC分类号： F01D5/284 , B22C9/04 , B22C9/10 , B23P15/04 , F01D5/182
摘要： A method of making at least the aerofoil of a blade for a gas turbine engine in which the cooling air exit passages, whether at the trailing edge or in other parts of the aerofoil, are cast rather than machined subsequently. In the method a disposable piece is formed with holes of the shape of the holes eventually required in the blade aerofoil. The piece is placed in a die and used to define part of the ceramic core required in the casting process, the die being arranged to produce a channel portion interconnecting the otherwise free ends of the parts of the core which will form the passages. The ceramic core thus formed in a lost-wax casting process to form the blade aerofoil, the channel portion being embedded in the shell mould to support the parts which define the passages.
摘要翻译：至少制造用于燃气涡轮发动机的叶片的翼型的方法，其中冷却空气出口通道，无论是在机翼的后缘还是在其它部分，都被铸造，而不是随后被加工。在该方法中，一次性片材形成有最终在叶片机翼中需要的孔的形状的孔。该片被放置在模具中并且用于限定铸造过程中所需的陶瓷芯的一部分，模具被布置成产生将形成通道的芯部分的其它自由端相互连接的通道部分。陶瓷芯由此形成在失蜡铸造工艺中以形成叶片机翼，通道部分嵌入壳模中以支撑限定通道的部件。

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