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1. 发明授权

US06733229B2 Insert metering plates for gas turbine nozzles 有权
标题翻译：插入燃气轮机喷嘴的计量板
公开(公告)号：US06733229B2
公开(公告)日：2004-05-11
申请号：US10092572
申请日：2002-03-08
申请人： Steven S. Burdgick , Gary Itzel , Sanjay Chopra , Nesim Abuaf , Victor H. Correia
发明人： Steven S. Burdgick , Gary Itzel , Sanjay Chopra , Nesim Abuaf , Victor H. Correia
IPC分类号： F01D906
CPC分类号： F01D5/189 , F01D9/065 , F05D2260/201
摘要： The invention comprises a metering plate which is assembled to an impingement insert for use in the nozzle of a gas turbine. The metering plate can have one or more metering holes and is used to balance the cooling flow within the nozzle. A metering plate with multiple holes reduces static pressure variations which result from the cooling airflow through the metering plate. The metering plate can be assembled to the insert before or after the insert is inserted into the nozzle.
摘要翻译：本发明包括计量板，其被组装到用于燃气轮机的喷嘴中的冲击插入件。计量板可以具有一个或多个计量孔，并用于平衡喷嘴内的冷却流。具有多个孔的计量板减少了由通过计量板的冷却气流引起的静压变化。在将插入件插入喷嘴之前或之后，计量盘可以组装到插入件上。

2. 发明申请

US20080014094A1 Coated bucket damper pin 失效
标题翻译：涂层斗风挡销
公开(公告)号：US20080014094A1
公开(公告)日：2008-01-17
申请号：US11902252
申请日：2007-09-20
申请人： Gary Itzel , Ariel Jacala , Doyle Lewis , Kathleen Morey , David Bucci , Ganjiang Feng
发明人： Gary Itzel , Ariel Jacala , Doyle Lewis , Kathleen Morey , David Bucci , Ganjiang Feng
IPC分类号： F01D5/30
CPC分类号： F01D5/22 , F01D5/26 , F05D2230/311 , F05D2230/312 , F05D2230/90 , F05D2250/141 , F05D2300/611 , Y10S416/50 , Y10T29/4932
摘要： A damper pin for a turbine bucket includes an elongated main body portion of substantially uniform cross-sectional shape having opposite ends, one only of said opposite ends coated with a corrosion and oxidation-resistant coating.
摘要翻译：用于涡轮机叶片的阻尼器销包括具有相对端部的基本均匀横截面形状的细长主体部分，仅一个所述相对端部涂覆有耐腐蚀和抗氧化涂层。

3. 发明申请

US20050169746A1 Film cooling for the trailing edge of a steam cooled nozzle 有权
标题翻译：蒸汽冷却喷嘴后缘的薄膜冷却
公开(公告)号：US20050169746A1
公开(公告)日：2005-08-04
申请号：US10771195
申请日：2004-02-03
申请人： Jason Fuller , Gary Itzel , Cathy Chiurato , Matthew Findlay
发明人： Jason Fuller , Gary Itzel , Cathy Chiurato , Matthew Findlay
IPC分类号： F01D5/18 , F01D9/02 , F01D25/12 , F03D11/00
CPC分类号： F01D5/186 , F01D9/02 , F01D25/12 , F05D2240/122 , F05D2240/304 , F05D2260/202 , F05D2260/205 , F05D2260/2322
摘要： A nozzle assembly (10) for a turbine engine includes an inner band (16) and an outer band (14) spaced apart from each other. An airfoil (12) installed between the bands has a leading edge (18) and a trailing edge (20). The airfoil has cavities formed in it for fluid flow through the nozzle assembly. A plurality of film cooling holes (1A-6H) are formed in a sidewall of the airfoil on a concave side of the assembly, and a plurality of film cooling holes (1J-1R) are formed in a sidewall of the nozzle on a convex side thereof. The holes are formed on each side of the airfoil, adjacent the trailing edge of the nozzle, in a plurality of rows of holes including at least a forward row (C, J), an aft row (A, L), and an intermediate row (B, K). The spacing between the intermediate row and aft row is substantially closer than the spacing between the forward row and the intermediate row.
摘要翻译：用于涡轮发动机的喷嘴组件（10）包括彼此间隔开的内带（16）和外带（14）。安装在带之间的翼型件（12）具有前缘（18）和后缘（20）。机翼具有形成在其中的空腔，用于流过喷嘴组件的流体。在组件的凹面上的翼型件的侧壁上形成有多个薄膜冷却孔（1A-6H），并且在该侧壁中形成多个薄膜冷却孔（1J-1R）喷嘴在其凸面上。所述孔形成在所述翼型件的与所述喷嘴的后缘相邻的每一侧上，所述多排排孔至少包括前排（C，J），后排（A，L）和中间体行（B，K）。中间行和后排之间的间隔基本上比前排和中间行之间的间距更近。

4. 发明申请

US20060285974A1 TURBINE BUCKET TIP CAP 有权
标题翻译：涡轮提篮盖
公开(公告)号：US20060285974A1
公开(公告)日：2006-12-21
申请号：US11160272
申请日：2005-06-16
申请人： Ronald Bunker , Gary Itzel
发明人： Ronald Bunker , Gary Itzel
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05C2201/0463 , F05C2201/0466 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141
摘要： A tip cap piece for use in a turbine bucket. The tip cap piece may include a cold side and a number of pins positioned on the cold side.
摘要翻译：用于涡轮机桶的顶盖件。尖端盖可以包括冷侧和位于冷侧的多个销。

5. 发明申请

US20060056969A1 Cooling system for the trailing edges of turbine bucket airfoils 有权
公开(公告)号：US20060056969A1
公开(公告)日：2006-03-16
申请号：US10940705
申请日：2004-09-15
申请人： Ariel Jacala , Gary Itzel , Joshua Kornau , Azadali Ladhani
发明人： Ariel Jacala , Gary Itzel , Joshua Kornau , Azadali Ladhani
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/122 , F05D2240/304 , F05D2260/202 , F05D2260/221 , Y02T50/673 , Y02T50/676
摘要： The cooling system includes a plurality of generally radially extending passages within the airfoil for convectively cooling the airfoil. A predetermined number of the passages exit through the airfoil tip. One or more of the remaining passages exit into a plenum adjacent the trailing edge and airfoil tip region of the airfoil and flow radially inwardly along one or more passageways adjacent the trailing edge region. The passageways exit in openings along the pressure side of the airfoil. In this manner, the trailing edge region is convectively cooled as well as film cooled by the film of air exiting the holes.

6. 发明申请

US20070189896A1 Methods and apparatus for cooling gas turbine rotor blades 有权
标题翻译：用于冷却燃气轮机转子叶片的方法和装置
公开(公告)号：US20070189896A1
公开(公告)日：2007-08-16
申请号：US11355213
申请日：2006-02-15
申请人： Gary Itzel , Ariel Jacala , Doyle Lewis , Calvin Sims
发明人： Gary Itzel , Ariel Jacala , Doyle Lewis , Calvin Sims
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2250/185 , F05D2260/205
摘要： Methods and apparatus for cooling rotor blades of a gas turbine are provided. The turbine blade has an airfoil connected to the platform and a dovetail extending from the platform. A main cooling circuit extends through the dovetail and into the airfoil. The main cooling circuit includes an exit for main cooling flow from the airfoil to exit out through the dovetail. In one aspect, the method includes the steps of extracting a portion of the coolant flowing through the main cooling circuit into a platform cooling circuit. After cooling a portion of the platform, the platform cooling flow splits with one portion of the flow rejoining the main cooling circuit and is used to cool the airfoil. The rest of the platform cooling flow continues to cool the platform and then returns to the main cooling circuit to flow through the exit.
摘要翻译：提供了一种用于冷却燃气轮机的转子叶片的方法和装置。涡轮叶片具有连接到平台的翼型件和从平台延伸的燕尾榫。主冷却回路延伸穿过燕尾榫并进入翼型。主冷却回路包括用于从翼型件主冷却流出的出口，通过燕尾出口。一方面，该方法包括以下步骤：将流经主冷却回路的冷却剂的一部分提取到平台冷却回路中。在冷却平台的一部分之后，平台冷却流将与流入主冷却回路的一部分流分开并用于冷却翼型。平台冷却流程的其余部分继续冷却平台，然后返回到主冷却回路以流过出口。

7. 发明申请

US20070224049A1 Steam-cooled gas turbine bucker for reduced tip leakage loss 有权
标题翻译：蒸汽式燃气轮机桶用于减少尖端泄漏损失
公开(公告)号：US20070224049A1
公开(公告)日：2007-09-27
申请号：US11228241
申请日：2005-09-19
申请人： Gary Itzel , Philip Andrew
发明人： Gary Itzel , Philip Andrew
IPC分类号： F03B3/12
CPC分类号： F01D5/20 , F01D5/288 , F01D11/122
摘要： A bucket for a steam turbine includes an airfoil portion having a radially outer tip, the radially outer tip having a thermal barrier coating applied thereto, and wherein the thermal barrier coating is resurfaced to form at least one ridge along the radially outer tip.
摘要翻译：用于蒸汽涡轮机的桶包括具有径向外部末端的翼型部分，径向外部末端具有施加到其上的热障涂层，并且其中所述热障涂层被重新表面以沿着径向外部尖端形成至少一个脊。

8. 发明申请

US20060257262A1 Coated bucket damper pin 有权
公开(公告)号：US20060257262A1
公开(公告)日：2006-11-16
申请号：US11127174
申请日：2005-05-12
申请人： Gary Itzel , Ariel Jacala , Doyle Lewis , Kathleen Morey , David Bucci , Ganjiang Feng
发明人： Gary Itzel , Ariel Jacala , Doyle Lewis , Kathleen Morey , David Bucci , Ganjiang Feng
IPC分类号： F01D5/30
CPC分类号： F01D5/22 , F01D5/26 , F05D2230/311 , F05D2230/312 , F05D2230/90 , F05D2250/141 , F05D2300/611 , Y10S416/50 , Y10T29/4932
摘要： A damper pin for a turbine bucket includes an elongated main body portion of substantially uniform cross-sectional shape having opposite ends, one only of said opposite ends coated with a corrosion and oxidation-resistant coating.

9. 发明申请

US20060140750A1 NOZZLE-COOLING INSERT ASSEMBLY WITH CAST-IN RIB SECTIONS 有权
标题翻译：喷嘴冷却插件组件与插入式RIB部分
公开(公告)号：US20060140750A1
公开(公告)日：2006-06-29
申请号：US10834925
申请日：2004-04-30
申请人： Steven Burdgick , Gary Itzel
发明人： Steven Burdgick , Gary Itzel
IPC分类号： F04D31/00
CPC分类号： F01D5/189 , Y02T50/676 , Y10T29/49343
摘要： A cooling insert/nozzle assembly for use in gas turbines or similar machinery includes a nozzle having inner and outer ribs with cast-in “T” sections and “L” sections, respectively, at the end of the ribs in which air flow enters the nozzle. The assembly further includes a cooling insert having a flexible end which is inserted between adjacent ribs having either the cast-in “T” or “L” sections.
摘要翻译：用于燃气轮机或类似机械的冷却插入件/喷嘴组件包括具有内肋和外肋的喷嘴，所述内肋和外肋分别在肋的末端分别具有“T”形截面和“L”形截面，其中气流进入喷嘴。组件还包括具有柔性端部的冷却插入件，所述柔性端部插入在具有铸入“T”或“L”部分的相邻肋之间。

10. 发明申请

US20050247425A1 METHOD AND APPARATUS FOR DETERMINING THE LOCATION OF CORE-GENERATED FEATURES IN AN INVESTMENT CASTING 有权
标题翻译：确定投资铸造中核心特征位置的方法和装置
公开(公告)号：US20050247425A1
公开(公告)日：2005-11-10
申请号：US10709451
申请日：2004-05-06
申请人： Robert Devine , Gary Itzel
发明人： Robert Devine , Gary Itzel
IPC分类号： B22C9/04 , B22C9/10 , B22C9/24 , B22D25/02 , B22D33/04
CPC分类号： B22C9/10
摘要： A secondary datum scheme is used for identifying the location of the core-produced internal geometry of hollow investment cast metal parts that are made using a free-floating core design for implementing complex internal structural features. A set of datum pads are cast on a removable portion of the core print out to provide the secondary reference system. This secondary reference system precisely establishes the location of the core-produced internal geometry of the part exclusive of any fixed external primary datum structure/system so that, for example, precision machining and gauging may be performed upon such internal features during subsequent fabrication steps.
摘要翻译：使用二次基准方案来识别使用自由浮动芯设计来实现复杂的内部结构特征的中空投资铸造金属部件的芯产生的内部几何形状的位置。一组基准垫被投射在核心打印输出的可移除部分上，以提供次要参考系统。该二次参考系统精确地建立了排除任何固定的外部主基准结构/系统的零件的内芯几何形状的位置，使得例如在随后的制造步骤期间可以对这些内部特征进行精密加工和测量。

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