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公开(公告)号：US07377746B2
公开(公告)日：2008-05-27
申请号：US11062001
申请日：2005-02-21
申请人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
发明人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
IPC分类号： F03D11/02
CPC分类号： F01D5/18 , B22C9/043 , F05D2230/21 , Y02T50/676 , Y10T29/49243 , Y10T29/49245
摘要： An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.
摘要翻译： 公开了一种具有至少第一和第二铸造，轴向堆叠的内部气流冷却回路的翼型件。 每个回路限定了多个气流通道，其横向位于各个电路的压力侧壁侧和吸力侧壁侧之间。 每个电路由单独的铸造芯形成。 还公开了形成轴向堆叠的芯和翼型的方法。
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公开(公告)号：US20080080979A1
公开(公告)日：2008-04-03
申请号：US11062001
申请日：2005-02-21
申请人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
发明人： Steven Robert Brassfield , Ching-Pang Lee , Roger Lee Doughty , Richard William Jendrix , Cory Michael Williams
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , B22C9/043 , F05D2230/21 , Y02T50/676 , Y10T29/49243 , Y10T29/49245
摘要： An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.
摘要翻译： 公开了一种具有至少第一和第二铸造，轴向堆叠的内部气流冷却回路的翼型件。 每个回路限定了多个气流通道，其横向位于各个电路的压力侧壁侧和吸力侧壁侧之间。 每个电路由单独的铸造芯形成。 还公开了形成轴向堆叠的芯和翼型的方法。
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公开(公告)号：US09033652B2
公开(公告)日：2015-05-19
申请号：US13250345
申请日：2011-09-30
申请人： Steve Mark Molter , Steven Robert Brassfield , Richard William Jendrix , Cory Michael Williams , Renee Solomon Wenstrup , Mark Willard Marusko , Mark Edward Stegemiller
发明人： Steve Mark Molter , Steven Robert Brassfield , Richard William Jendrix , Cory Michael Williams , Renee Solomon Wenstrup , Mark Willard Marusko , Mark Edward Stegemiller
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.
摘要翻译： 用于燃气涡轮发动机的翼型件包括在前缘和后缘处联接在一起的第一侧壁和第二侧壁，使得在其间限定空腔。 多个冷却回路被限定在空腔内。 每个冷却回路使冷却流体通过至少一个冷却室，以便冷却翼型件。 更具体地，提供了级联冲击电路，降压电路，标记尖端电路和后沿电路。 级联冲击电路包括中央室和多个冲击室。
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公开(公告)号：US20130081408A1
公开(公告)日：2013-04-04
申请号：US13250345
申请日：2011-09-30
申请人： Steve Mark Molter , Steven Robert Brassfield , Richard William Jendrix , Cory Michael Williams , Renee Solomon Wenstrup , Mark Willard Marusko , Mark Edward Stegemiller
发明人： Steve Mark Molter , Steven Robert Brassfield , Richard William Jendrix , Cory Michael Williams , Renee Solomon Wenstrup , Mark Willard Marusko , Mark Edward Stegemiller
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.
摘要翻译： 用于燃气涡轮发动机的翼型件包括在前缘和后缘处联接在一起的第一侧壁和第二侧壁，使得在其间限定空腔。 多个冷却回路被限定在空腔内。 每个冷却回路使冷却流体通过至少一个冷却室，以便冷却翼型件。 更具体地，提供了级联冲击电路，降压电路，标记尖端电路和后沿电路。 级联冲击电路包括中央室和多个冲击室。
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5.发明申请HYBRID CERAMIC MATRIX COMPOSITE TURBINE BLADES FOR IMPROVED PROCESSIBILITY AND PERFORMANCE AND PROCESS FOR PRODUCING HYBRID TURBINE BLADES 审中-公开混合陶瓷基体复合涡轮叶片，用于改进混合涡轮叶片的可行性和性能及工艺公开(公告)号：US20110229337A1
公开(公告)日：2011-09-22
申请号：US12828266
申请日：2010-06-30
CPC分类号： C04B35/565 , B32B18/00 , B32B2311/22 , B32B2315/02 , C04B35/62863 , C04B35/62868 , C04B35/62871 , C04B35/62873 , C04B2235/422 , C04B2235/428 , C04B2235/5244 , C04B2235/5248 , C04B2235/5256 , C04B2235/5268 , C04B2235/616 , C04B2235/80 , C04B2237/361 , C04B2237/363 , C04B2237/365 , C04B2237/368 , C04B2237/38 , C04B2237/61 , F01D5/282 , F01D5/284 , F05D2300/2261 , F05D2300/603 , Y02T50/67 , Y02T50/672
摘要： The present invention is a hybrid ceramic matrix composite turbine engine component comprising an outer shell section(s) and an inner core section(s), wherein the outer shell section(s) and the inner core section(s) were bonded together using a melt infiltration (MI) process. The outer shell section(s) comprises a SiC/SiC material that has been manufactured using a process selected from the group consisting of a slurry cast MI process and a prepreg MI process. The inner core section(s) comprises a material selected from the group consisting an Si/SiC composite material and a monolithic ceramic material. The Si/SiC composite material may be manufactured using the Silcomp process. The present invention may be a high pressure turbine blade, a high pressure turbine vane, a low pressure turbine blade, or a low pressure turbine vane. The present invention is also a method of manufacturing a hybrid ceramic matrix composite turbine engine component.
摘要翻译： 本发明是一种混合陶瓷基复合涡轮发动机部件，其包括外壳部分和内芯部分，其中外壳部分和内芯部分使用 熔融渗透（MI）工艺。 外壳部分包括使用选自淤浆浇铸MI工艺和预浸料MI工艺的工艺制造的SiC / SiC材料。 内芯部分包括选自Si / SiC复合材料和单块陶瓷材料的材料。 Si / SiC复合材料可以使用Silcomp工艺制造。 本发明可以是高压涡轮叶片，高压涡轮叶片，低压涡轮叶片或低压涡轮叶片。 本发明也是制造混合陶瓷基复合涡轮发动机部件的方法。
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6.发明授权公开(公告)号：US07341429B2
公开(公告)日：2008-03-11
申请号：US11280439
申请日：2005-11-16
申请人： Julius John Montgomery , Robert Proctor , Nathan Gerard Cormier , Christopher Charles Glynn , Glen William Royal , Richard William Jendrix
发明人： Julius John Montgomery , Robert Proctor , Nathan Gerard Cormier , Christopher Charles Glynn , Glen William Royal , Richard William Jendrix
IPC分类号： F03B11/00
CPC分类号： F01D5/082 , F05D2250/70 , F05D2260/201
摘要： A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the turbine mid-frame, and forming at least one opening extending through the turbine mid-frame to facilitate channeling cooling air into the gap, the opening configured to impart a high relative tangential velocity into the cooling air discharged from the opening.
摘要翻译： 一种制造燃气涡轮发动机的方法包括提供涡轮机中间框架，将多个转子叶片耦合到转子盘，转子盘从涡轮机中间框架轴向后部被连接，使得在转子盘 和涡轮机中间框架，并且形成延伸穿过涡轮机中间框架的至少一个开口，以便于将冷却空气引导到间隙中，该开口构造成将高的相对切向速度赋予从开口排出的冷却空气。
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