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1. 发明授权

US06261054B1 Coolable airfoil assembly 有权
标题翻译：可冷却翼型组件
公开(公告)号：US06261054B1
公开(公告)日：2001-07-17
申请号：US09235914
申请日：1999-01-25
申请人： Ronald Scott Bunker , James William Bartos , Nicholas Damlis , Mark Eugene Noe , Steven Douglas Ward
发明人： Ronald Scott Bunker , James William Bartos , Nicholas Damlis , Mark Eugene Noe , Steven Douglas Ward
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2220/20 , F05D2220/31 , F05D2220/32 , F05D2260/201 , F05D2260/232 , F05D2260/2322 , Y02T50/676
摘要： An apparatus and method including a closed-circuit coolable airfoil assembly for use and exposure in a hot fluid flow of a machine portion. The assembly includes a first flange configured to be connected with a casing of the machine portion. A second flange is configured to be connected with the casing. An airfoil is connected with and between the first flange and the second flange, the airfoil including a peripheral portion surrounding a medial portion. At least one channel is disposed in the peripheral portion, the channel extending between the first flange and the second flange and being in flow communication with each. A closed flow path is formed from the casing and through the first flange, the second flange and the channel in which a coolant fluid can pass to cool the airfoil assembly.
摘要翻译：一种装置和方法，包括用于在机器部分的热流体流中使用和暴露的闭路冷却翼型组件。组件包括构造成与机器部分的壳体连接的第一凸缘。第二凸缘被构造成与壳体连接。翼型件与第一凸缘和第二凸缘之间连接并且在第一凸缘和第二凸缘之间，翼型件包括围绕中间部分的周边部分。至少一个通道设置在周边部分中，该通道在第一凸缘和第二凸缘之间延伸并且与每个通道流动连通。从壳体和第一凸缘，第二凸缘和冷却剂流体可以通过的通道形成封闭的流动路径，以冷却翼型组件。

2. 发明授权

US06484508B2 Methods for operating gas turbine engines 有权
标题翻译：操作燃气涡轮发动机的方法
公开(公告)号：US06484508B2
公开(公告)日：2002-11-26
申请号：US09899714
申请日：2001-07-05
申请人： Mark Stephen Rocklin , Nicholas Damlis , Curtis Lee Brown , Robert Paul Coleman , James William Stegmaier
发明人： Mark Stephen Rocklin , Nicholas Damlis , Curtis Lee Brown , Robert Paul Coleman , James William Stegmaier
IPC分类号： F02C330
CPC分类号： F01K21/047 , F02C3/305 , F02C7/1435 , F02C7/224 , F02C9/48 , F04D29/705 , F05D2270/303
摘要： A method is provided for operating a gas turbine engine that includes a high pressure compressor and a water injection apparatus for injecting water into a flow of the engine upstream from the high pressure compressor. The method includes the steps of operating the engine without injecting water into the gas flow of the engine, injecting water at a first flow rate into the gas flow for power augmentation once engine full power is about reached, and injecting water into the engine at an increased second flow rate for evaporative cooling of engine components downstream from the high pressure compressor.
摘要翻译：提供了一种用于操作燃气涡轮发动机的方法，该燃气涡轮发动机包括高压压缩机和用于将水注入高压压缩机上游的发动机流的注水装置。该方法包括以下步骤：一旦发动机全部功率达到，操作发动机而不向发动机的气流中注入水，并将第一流量的水喷射到用于动力增加的气流中，并且以一增加用于从高压压缩机下游的发动机部件的蒸发冷却的第二流量。

3. 发明授权

US5228828A Gas turbine engine clearance control apparatus 失效
标题翻译：燃气轮机发动机间隙控制装置
公开(公告)号：US5228828A
公开(公告)日：1993-07-20
申请号：US656275
申请日：1991-02-15
申请人： Nicholas Damlis , Frederick J. Zegarski , Donald D. Brayton
发明人： Nicholas Damlis , Frederick J. Zegarski , Donald D. Brayton
IPC分类号： F01D11/10 , F01D11/08 , F01D11/22 , F02C7/28
CPC分类号： F01D11/22
摘要： Apparatus for controlling the clearance between the tips of a row of rotor blades and an array of surrounding shroud segments in a gas turbine engine. A torque tube is rotatably mounted on the engine casing and has a cam positioned inside the casing. First and second members are positioned inside the casing so as to be only axially moveable and so as to have their cam-engaging surfaces axially surround the cam, and they are biased such that the cam-engaging surfaces engage the cam. A shroud hanger, to which a shroud segment may be attached, includes axially spaced apart hooked flanges positioned to be engaged by hooked flanges of the first and second members. The flanges have axially inclined slide surfaces for such engagement, and the shroud hanger is biased radially inward to engage such slide surfaces. Clearance is controlled by rotation of the torque tube which axially moves the first and second members which radially moves the shroud segment.
摘要翻译：用于控制一排转子叶片的尖端与燃气涡轮发动机中的周围的护罩段阵列之间的间隙的装置。扭矩管可旋转地安装在发动机壳体上并且具有定位在壳体内的凸轮。第一和第二构件定位在壳体内部，以便仅可轴向移动并且使其凸轮接合表面轴向地围绕凸轮，并且它们被偏置，使得凸轮接合表面接合凸轮。可以安装护罩段的护罩悬挂器包括轴向间隔开的钩状凸缘，其被定位成与第一和第二构件的钩形凸缘接合。凸缘具有用于这种接合的轴向倾斜的滑动表面，并且护罩悬挂器径向向内偏置以接合这种滑动表面。间隙通过扭矩管的旋转来控制，扭矩管轴向地移动使径向移动护罩段的第一和第二构件。

4. 发明授权

US06546735B1 Methods and apparatus for operating turbine engines using rotor temperature sensors 有权
标题翻译：使用转子温度传感器操作涡轮发动机的方法和装置
公开(公告)号：US06546735B1
公开(公告)日：2003-04-15
申请号：US09801121
申请日：2001-03-07
申请人： Thomas Moniz , Nicholas Damlis , Jack Willard Smith, Jr. , Joseph Henry Schleue , Donald Ray Bond
发明人： Thomas Moniz , Nicholas Damlis , Jack Willard Smith, Jr. , Joseph Henry Schleue , Donald Ray Bond
IPC分类号： F02C900
CPC分类号： F01D9/065 , F01D17/085 , F01D21/003 , F02C9/00 , F05D2270/303 , F05D2270/3032
摘要： A gas turbine engine including a temperature sensor assembly that continuously monitors an operating temperature within a multi-stage rotor assembly of the turbine engine is described. A plurality of cavities are defined within the multi-stage rotor assembly. The temperature sensor assembly includes a plurality of temperature sensor assemblies that monitor the temperature within each of the rotor assembly cavities. Each temperature sensor assembly includes a plurality of support guide tubes attached to the engine and extending from an outer casing of the engine to each cavity. A temperature sensor is inserted through the guide tubes and positioned within each cavity.
摘要翻译：描述了包括连续监测涡轮发动机的多级转子组件内的工作温度的温度传感器组件的燃气涡轮发动机。在多级转子组件内限定多个空腔。温度传感器组件包括多个温度传感器组件，其监测每个转子组件空腔内的温度。每个温度传感器组件包括附接到发动机并从发动机的外壳延伸到每个空腔的多个支撑引导管。温度传感器通过导管插入并定位在每个空腔内。

5. 发明授权

US06438941B1 Bifurcated splitter for variable bleed flow 有权
标题翻译：分流式分流器，用于可变流量
公开(公告)号：US06438941B1
公开(公告)日：2002-08-27
申请号：US09843565
申请日：2001-04-26
申请人： Dale Bradley Elliott , Peter Nicholas Szucs , Nicholas Damlis , Kenneth Paul Onderko
发明人： Dale Bradley Elliott , Peter Nicholas Szucs , Nicholas Damlis , Kenneth Paul Onderko
IPC分类号： F02K302
CPC分类号： F02C9/18 , F01D17/105 , F02C6/08 , F04D27/023 , F04D29/545
摘要： An air bleed assembly for extracting air from a flowpath in a gas turbine engine includes a casing for surrounding a row of circumferentially spaced apart rotor blades and defining at least in part the flowpath for receiving air compressed by the rotor blades. The casing includes a bleed port disposed downstream of a row of the blades for receiving a portion of the compressed air as bleed airflow and a bleed duct extending away from the bleed port. The bleed duct has an annular slot in the casing. The annular slot has annular slot leading and trailing edges and an annular bifurcated splitter disposed along at least a portion of the annular slot trailing edge. The bifurcated splitter has an annular leading edge forebody located upstream of and separated from an annular splitter wall by an annular return channel. In one embodiment of the invention, the rotor blades are fan blades and the annular bleed space is in the flowpath in a fan section of the engine. The annular bleed space is located between a fan variable vane disposed across the flowpath and one of the fan blades located downstream of the fan variable vane.
摘要翻译：用于从燃气涡轮发动机的流路中提取空气的排气组件包括用于围绕一排周向间隔开的转子叶片的壳体，并且至少部分限定用于接收由转子叶片压缩的空气的流路。壳体包括设置在一排叶片下游的排出口，用于接收一部分压缩空气作为排出气流，以及从排出口延伸的排放管。排气管在壳体中具有环形槽。环形槽具有环形槽前缘和后缘以及沿着环形槽后缘的至少一部分设置的环形分叉分流器。分叉式分流器具有通过环形返回通道位于环形分隔壁上游并与环形分隔壁分离的环形前缘前体。在本发明的一个实施例中，转子叶片是风扇叶片，并且环形排出空间位于发动机的风扇部分的流路中。环形排出空间位于跨过流路设置的风扇可变叶片和位于风扇可变叶片下游的风扇叶片之一之间。

6. 发明授权

US06202277B1 Reusable hard tooling for article consolidation and consolidation method 有权
标题翻译：文章整合和整合方法的可重用硬工具
公开(公告)号：US06202277B1
公开(公告)日：2001-03-20
申请号：US09429284
申请日：1999-10-28
申请人： Ahmad P. Zahedi , Nicholas Damlis , Paul A. Siemers
发明人： Ahmad P. Zahedi , Nicholas Damlis , Paul A. Siemers
IPC分类号： B23P1700
CPC分类号： B23K20/24 , B22F3/1241 , B23K20/02 , B23K20/26 , B29C37/0075 , Y10T29/4981 , Y10T428/24942
摘要： Hard tooling for consolidation of a workpiece there between is preserved for reuse by disposing between the tooling and a workpiece a plurality of distinct, superimposed sacrificial sheets, for example metal foils, to isolate the workpiece from the tooling. The sacrificial sheets are substantially non-adherent one to another; and a sheet in contact with a workpiece surface is substantially chemically non-reactive with such workpiece surface.
摘要翻译：通过在工具和工件之间布置多个不同的叠加的牺牲片（例如金属箔），将工件与工具隔离，用于固定其间的工件的硬工具被保留以供再利用。牺牲片基本上是非粘附的; 并且与工件表面接触的片材基本上与这种工件表面化学地不反应。

7. 发明授权

US5516260A Bonded turbine airfuel with floating wall cooling insert 失效
标题翻译：保税涡轮空气与浮动壁冷却插入
公开(公告)号：US5516260A
公开(公告)日：1996-05-14
申请号：US320096
申请日：1994-10-07
申请人： Nicholas Damlis , Anne M. Isburgh , James A. Martus , Edward H. Goldman
发明人： Nicholas Damlis , Anne M. Isburgh , James A. Martus , Edward H. Goldman
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/189
摘要： A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with a radially extending airfoil having an outer wall surrounding at least one radially extending cavity and extending chordwise through at least a portion of the airfoil. The outer wall has ribs disposed on an inner surface of the outer wall and cooling passages formed between the outer wall and an insert disposed in the cavity against and in abutting sealing relationship with the ribs, wherein the outer wall is formed from two radially and chordwise extending sections, preferably suction and pressure side sections, bonded together while the insert was disposed inside the cavity. The insert provides an inner wall surrounding a hollow chamber generally conforming to the cavity the insert is disposed in and the insert includes a spring to force the inner wall out against the ribs during the bonding process.
摘要翻译：用于燃气涡轮发动机部件如涡轮机叶片或叶片的可冷却翼型设置有径向延伸的翼型件，其具有包围至少一个径向延伸的空腔的外壁，并且延伸通过翼型的至少一部分延伸。外壁具有设置在外壁的内表面上的肋和形成在外壁和布置在空腔内的插入件之间的冷却通道，与肋抵接和抵接密封关系，其中外壁由径向和弦向两个形成延伸部分，优选是吸入和压力侧部分，当插入件设置在腔内时，粘合在一起。插入件提供围绕中空室的内壁，该中空室通常与嵌入件所设置的空腔相一致，并且插入件包括弹簧，以在接合过程中迫使内壁抵靠肋。

8. 发明授权

US5259730A Impingement cooled airfoil with bonding foil insert 失效
标题翻译：用粘合箔插入件冲压冷却翼型
公开(公告)号：US5259730A
公开(公告)日：1993-11-09
申请号：US15872
申请日：1993-02-10
申请人： Nicholas Damlis , James A. Martus , Edward H. Goldman
发明人： Nicholas Damlis , James A. Martus , Edward H. Goldman
IPC分类号： B23P15/04 , F01D5/18
CPC分类号： F01D5/189 , B23P15/04 , F05D2260/201
摘要： An impinqement cooled airfoil is fabricated by diffusion bonding a pair of airfoil half-sections together using an insert which is prefabricated from diffusion bonding foil. The insert is perforated so as to act as an impingement baffle. Axially-extending ribs may be formed on the internal walls of the airfoil half-sections or on the insert to support and accurately space the insert member from the internal walls so as to optimize impingement cooling.
摘要翻译：通过使用从扩散接合箔预制的插入件将一对翼型半部分扩散接合在一起，制造出不可思议的冷却翼型件。插入件穿孔以作为冲击挡板。轴向延伸肋可以形成在翼型件半部分的内壁上或插入件上，以支撑和准确地将插入构件从内壁空间排出，以便优化冲击冷却。

9. 发明授权

US5176499A Photoetched cooling slots for diffusion bonded airfoils 失效
标题翻译：用于扩散粘结的飞行器的光刻冷却滑块
公开(公告)号：US5176499A
公开(公告)日：1993-01-05
申请号：US719901
申请日：1991-06-24
申请人： Nicholas Damlis , James A. Martus , Edward H. Goldman
发明人： Nicholas Damlis , James A. Martus , Edward H. Goldman
IPC分类号： B23K20/00 , B23P15/04 , C23F4/00 , F01D5/18 , F01D9/02
CPC分类号： B23P15/04 , F01D5/188 , Y10T29/49243
摘要： Cooling passages are accurately formed along the faying surfaces of a pair of diffusion bonded members such as a pair of half sections used to fabricate an airfoil. A particularly advantageous application of the invention is the photoetching of cooling air grooves into the opposed surfaces of a diffusion bonding foil used to form a diffusion bond between the faying surfaces of a trailing edge portion of a turbine blade or turbine vane. Such grooves may be made extremely small and in high numbers to promote efficient cooling of the trailing edge portions of these airfoils.

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