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公开(公告)号：US20140271146A1
公开(公告)日：2014-09-18
申请号：US14184780
申请日：2014-02-20
Applicant: DOUGLAS JAMES DIETRICH , KEVIN DAMIAN CARPENTER
Inventor： DOUGLAS JAMES DIETRICH , KEVIN DAMIAN CARPENTER
CPC classification number: F04D29/644 , F01D5/3046 , F01D5/32 , F04D29/083 , F04D29/542 , Y10T29/49236
Abstract: The present invention relates to a system and method for joining adjacent sections of a compressor diaphragm. A splitline jumper is positioned within a recessed portion of a seal ring segment of the adjacent compressor diaphragms. The splitline jumper is sized and oriented so as to prevent axial movement of the compressor diaphragms relative to each other and also to prevent rotational movement of the seal ring relative to the diaphragm.
Abstract translation: 本发明涉及一种用于连接压缩机隔膜的相邻部分的系统和方法。 分流跳线定位在相邻压缩机隔膜的密封环段的凹陷部分内。 分流式跳线的尺寸和取向是为了防止压缩机隔膜相对于彼此的轴向移动，并且还防止密封环相对于隔膜的旋转运动。
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公开(公告)号：US08550783B2
公开(公告)日：2013-10-08
申请号：US13078664
申请日：2011-04-01
Applicant: Douglas James Dietrich , Stephen Wayne Fiebiger , Gregory Edwin Vogel
Inventor： Douglas James Dietrich , Stephen Wayne Fiebiger , Gregory Edwin Vogel
IPC: F01D5/30
CPC classification number: F01D5/147 , F01D5/187 , F05D2230/10 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2240/81 , F05D2270/114
Abstract: A system and method of extending the useable life of a gas turbine blade is disclosed in which the gas turbine blade includes an undercut configuration designed to relieve mechanical and thermal stress imparted into the pedestal region of the airfoil trailing edge. The embodiments of the present invention include turbine blade configurations having different trailing edge undercut configurations as well as additional cooling supplied to the internal passages of the trailing edge region of the turbine blade.
Abstract translation: 公开了一种延长燃气轮机叶片的使用寿命的系统和方法，其中燃气轮机叶片包括设计成减轻施加到翼型后缘的基座区域中的机械和热应力的底切构型。 本发明的实施例包括具有不同后缘底切构造的涡轮叶片构造以及供应到涡轮叶片的后缘区域的内部通道的附加冷却。
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公开(公告)号：US6068806A
公开(公告)日：2000-05-30
申请号：US34665
申请日：1998-03-04
Applicant: Douglas James Dietrich
Inventor： Douglas James Dietrich
CPC classification number: B29C33/301 , B22C9/10 , B22C9/103 , B29C33/76 , B29C33/42 , B29C35/16 , B29L2031/08 , F01D5/187 , Y10T29/49341
Abstract: The internally air cooled turbine cast blade is molded with a ceramic core for defining the interior cavity with coolant passages where the ceramic core is configured to fair radially inwardly at the attachment portion of the blade until they form a single wall, parallel to and centered in the blade attachment. The blade is cast in the mold by pouring molten metal into the mold, curing and the core is leached once the metal is cured and the mold removed. Another embodiment includes a metering plate attached to the root of the blade for metering coolant to provide a coolant to gas flow ratio at the film cooling holes.
Abstract translation: 内部空气冷却的涡轮铸造叶片模制有陶瓷芯，用于通过冷却剂通道限定内部空腔，其中陶瓷芯被构造成在叶片的附接部分处径向向内展开，直到它们形成平行于并居中的单个壁 刀片附件。 刀片通过将熔融金属浇注到模具中而在模具中铸造，固化并且一旦金属固化并且模具被去除就将铁芯浸出。 另一个实施例包括附接到叶片的根部的计量板，用于计量冷却剂以在薄膜冷却孔处提供冷却剂至气体流量比。
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公开(公告)号：US10443389B2
公开(公告)日：2019-10-15
申请号：US15808415
申请日：2017-11-09
Applicant: Douglas James Dietrich , Jeff Tessier , Megan Burke , Stephen Wayne Fiebiger , Roy E. Struble , Christopher Charles Williams , Alexander Vasili Rozendaal , Lonnie Adolphus Houck, III
Inventor： Douglas James Dietrich , Jeff Tessier , Megan Burke , Stephen Wayne Fiebiger , Roy E. Struble , Christopher Charles Williams , Alexander Vasili Rozendaal , Lonnie Adolphus Houck, III
Abstract: A turbine blade, airfoil, and rotor stage for a gas turbine engine is disclosed. The turbine blade, airfoil, and rotor stage each includes an uncoated airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z disclosed herein. The resulting airfoil exhibits high flutter margins, thus enabling the gas turbine engine to be operated at an increased power output while avoiding operational limitations required in known gas turbine engines.
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5.发明授权Turbine blade having improved flutter capability and increased turbine stage output 有权涡轮叶片具有改善的颤动能力和增加的涡轮级输出公开(公告)号：US08821125B2
公开(公告)日：2014-09-02
申请号：US13366532
申请日：2012-02-06
Applicant: Adam Lee Hart , Adam John Fredmonski , Douglas James Dietrich , Samer Abdel-Wahab , Stephen Wayne Fiebiger , Kuo-Ting Hsia , W. David Day , Richard Ramirez
Inventor： Adam Lee Hart , Adam John Fredmonski , Douglas James Dietrich , Samer Abdel-Wahab , Stephen Wayne Fiebiger , Kuo-Ting Hsia , W. David Day , Richard Ramirez
CPC classification number: F01D5/141 , F01D5/16 , F01D5/225 , F01D5/288 , F01D11/006 , F05D2250/74 , F05D2300/175
Abstract: A turbine blade, airfoil configuration, and rotor stage are disclosed in which through the airfoil profile disclosed in Table 1, a modification in airfoil flutter and swirl are achieved. Through the airfoil configuration, the swirl and improved platform sealing configuration, result in the turbine blades having the airfoil profile with an increased performance output from the turbine.
Abstract translation: 公开了一种涡轮叶片，翼型构造和转子级，其中通过表1中公开的翼型来实现翼型振动和涡流的改进。 通过翼型构造，涡流和改进的平台密封结构使得涡轮机叶片具有翼型轮廓，其具有来自涡轮机的增加的性能输出。
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Patent Agency Ranking
6.发明申请TURBINE BLADE HAVING IMPROVED FLUTTER CAPABILITY AND INCREASED TURBINE STAGE OUTPUT 有权具有改进的涡轮机能力和增加的涡轮机级输出的涡轮叶片公开(公告)号：US20130202445A1
公开(公告)日：2013-08-08
申请号：US13366532
申请日：2012-02-06
Applicant: ADAM LEE HART , ADAM JOHN FREDMONSKI , DOUGLAS JAMES DIETRICH , SAMER ABDEL-WAHAB , STEPHEN WAYNE FIEBIGER , KUO-TING HSIA , W. DAVID DAY
Inventor： ADAM LEE HART , ADAM JOHN FREDMONSKI , DOUGLAS JAMES DIETRICH , SAMER ABDEL-WAHAB , STEPHEN WAYNE FIEBIGER , KUO-TING HSIA , W. DAVID DAY , RICHARD RAMIREZ
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/16 , F01D5/225 , F01D5/288 , F01D11/006 , F05D2250/74 , F05D2300/175
Abstract: A turbine blade, airfoil configuration, and rotor stage are disclosed in which through the airfoil profile disclosed in Table 1, a modification in airfoil flutter and swirl are achieved. Through the airfoil configuration, the swirl and improved platform sealing configuration, result in the turbine blades having the airfoil profile with an increased performance output from the turbine.
Abstract translation: 公开了一种涡轮叶片，翼型构造和转子级，其中通过表1中公开的翼型来实现翼型振动和涡流的改进。 通过翼型构造，涡流和改进的平台密封结构，导致涡轮机叶片具有翼型轮廓，其具有来自涡轮机的增加的性能输出。
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公开(公告)号：US5951256A
公开(公告)日：1999-09-14
申请号：US34654
申请日：1998-06-22
Applicant: Douglas James Dietrich
Inventor： Douglas James Dietrich
CPC classification number: B29C33/301 , B22C9/10 , B22C9/103 , B29C33/76 , B29C33/42 , B29C35/16 , B29L2031/08 , F01D5/187 , Y10T29/49341
Abstract: The internally air cooled turbine cast blade is molded with a ceramic core for defining the interior cavity with coolant passages where the ceramic core is configured to fair radially inwardly at the attachment portion of the blade until they form a single wall, parallel to and centered in the blade attachment. The blade is cast in the mold by pouring molten metal into the mold, curing and the core is leached once the metal is cured and the mold removed. Another embodiment includes a metering plate attached to the root of the blade for metering coolant to provide a coolant to gas flow ratio at the film cooling holes.
Abstract translation: 内部空气冷却的涡轮铸造叶片模制有陶瓷芯，用于通过冷却剂通道限定内部空腔，其中陶瓷芯被构造成在叶片的附接部分处径向向内展开，直到它们形成平行于并居中的单个壁 刀片附件。 刀片通过将熔融金属浇注到模具中而在模具中铸造，固化并且一旦金属固化并且模具被去除就将铁芯浸出。 另一个实施例包括附接到叶片的根部的计量板，用于计量冷却剂以在薄膜冷却孔处提供冷却剂至气体流量比。
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公开(公告)号：US5820774A
公开(公告)日：1998-10-13
申请号：US689983
申请日：1996-10-28
Applicant: Douglas James Dietrich
Inventor： Douglas James Dietrich
CPC classification number: B29C33/301 , B22C9/10 , B22C9/103 , B29C33/76 , B29C33/42 , B29C35/16 , B29L2031/08 , F01D5/187 , Y10T29/49341
Abstract: The internally air cooled turbine cast blade is molded with a ceramic core for defining the interior cavity with coolant passages where the ceramic core is configured to fair radially inwardly at the attachment portion of the blade until they form a single wall, parallel to and centered in the blade attachment. The blade is cast in the mold by pouring molten metal into the mold, curing and the core is leached once the metal is cured and the mold removed. Another embodiment includes a metering plate attached to the root of the blade for metering coolant to provide a coolant to gas flow ratio at the film cooling holes.
Abstract translation: 内部空气冷却的涡轮铸造叶片模制有陶瓷芯，用于通过冷却剂通道限定内部空腔，其中陶瓷芯被构造成在叶片的附接部分处径向向内展开，直到它们形成平行于并居中的单个壁 刀片附件。 刀片通过将熔融金属浇注到模具中而在模具中铸造，固化并且一旦金属固化并且模具被去除就将铁芯浸出。 另一个实施例包括附接到叶片的根部的计量板，用于计量冷却剂以在薄膜冷却孔处提供冷却剂至气体流量比。
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公开(公告)号：US20190136696A1
公开(公告)日：2019-05-09
申请号：US15808415
申请日：2017-11-09
Applicant: Douglas James Dietrich , Jeff Tessier , Megan Burke , Stephen Wayne Fiebiger , Roy E. Struble , Christopher Charles Williams , Alexander Vasili Rozendaal , Lonnie Adolphus Houck, III
Inventor： Douglas James Dietrich , Jeff Tessier , Megan Burke , Stephen Wayne Fiebiger , Roy E. Struble , Christopher Charles Williams , Alexander Vasili Rozendaal , Lonnie Adolphus Houck, III
CPC classification number: F01D5/12 , F01D11/006 , F05D2250/74 , F05D2300/611
Abstract: A turbine blade, airfoil, and rotor stage for a gas turbine engine is disclosed. The turbine blade, airfoil, and rotor stage each includes an uncoated airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z disclosed herein. The resulting airfoil exhibits high flutter margins, thus enabling the gas turbine engine to be operated at an increased power output while avoiding operational limitations required in known gas turbine engines.
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公开(公告)号：US20120251331A1
公开(公告)日：2012-10-04
申请号：US13078664
申请日：2011-04-01
Applicant: Douglas James Dietrich , Stephen Wayne Fiebiger , Gregory Edwin Vogel
Inventor： Douglas James Dietrich , Stephen Wayne Fiebiger , Gregory Edwin Vogel
IPC: F01D5/18
CPC classification number: F01D5/147 , F01D5/187 , F05D2230/10 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2240/81 , F05D2270/114
Abstract: A system and method of extending the useable life of a gas turbine blade is disclosed in which the gas turbine blade includes an undercut configuration designed to relieve mechanical and thermal stress imparted into the pedestal region of the airfoil trailing edge. The embodiments of the present invention include turbine blade configurations having different trailing edge undercut configurations as well as additional cooling supplied to the internal passages of the trailing edge region of the turbine blade.
Abstract translation: 公开了一种延长燃气轮机叶片的使用寿命的系统和方法，其中燃气轮机叶片包括设计成减轻施加到翼型后缘的基座区域中的机械和热应力的底切构型。 本发明的实施例包括具有不同后缘底切构造的涡轮叶片构造以及供应到涡轮叶片的后缘区域的内部通道的附加冷却。
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