公开(公告)号：US20090263249A1

公开(公告)日：2009-10-22

申请号：US12227468

申请日：2007-02-23

Applicant: Torsten-Ulf Kern

Inventor： Torsten-Ulf Kern

IPC: F01D5/02

CPC classification number: F01D5/063 ,  C22C38/04 ,  C22C38/44 ,  C22C38/46 ,  F01D5/28 ,  F05C2201/0466 ,  F05D2300/131 ,  F05D2300/132 ,  Y10S464/902

Abstract: Turbo-engine which has a low-pressure area, containing at least one shaft, wherein the low-pressure area has an inflow area, the shaft having, at least on its inflow part arranged in the inflow area, a heat resistant material, wherein the shaft has, on outflow parts arranged opposite the inflow part, a 26NiCrV14-5 and/or 2SNiCrMoVii-5 and/or 22CrNiM09-9 material.

Abstract translation: 具有低压区域的涡轮发动机，其包含至少一个轴，其中所述低压区域具有流入区域，所述轴至少在其流入部分中布置在流入区域中，具有耐热材料，其中 轴在与流入部分相对的流出部分上具有26NiCrV14-5和/或2SNiCrMoVii-5和/或22CrNiM09-9材料。

公开(公告)号：US20090238684A1

公开(公告)日：2009-09-24

申请号：US11514745

申请日：2006-08-31

Applicant: Jay A. Morrison ,  Jay E. Lane

Inventor： Jay A. Morrison ,  Jay E. Lane

IPC: F01D25/12 ,  F01D25/14 ,  F01D5/18

CPC classification number: F01D5/187 ,  F01D5/288 ,  F01D25/12 ,  F05C2201/0466 ,  F05D2260/201 ,  F05D2300/122 ,  F05D2300/141 ,  F05D2300/172 ,  F05D2300/222 ,  F05D2300/224 ,  F05D2300/2262 ,  F05D2300/5024 ,  F05D2300/603 ,  F23R3/007 ,  F23R2900/03044

Abstract: A CMC wall (22) with a front surface (21) heated (24) by a working fluid in a gas turbine. A back CMC surface (23) is coated with a layer (42) of a thermally conductive material to accelerate heat transfer in the plane of the CMC wall (22), reducing thermal gradients (32-40) on the back CMC surface (23) caused by cold spots (32) resulting from impingement cooling flows (26). The conductive material (42) may have a coefficient of thermal conductivity at least 10 times greater than that of the CMC material (22), to provide a minimal thickness conductive layer (42). This reduces thermal gradient stresses within the CMC material (22), and minimizes differential thermal expansion stresses between the CMC material (22) and the thin conductive layer (42).

Abstract translation: 具有通过燃气轮机中的工作流体加热（24）的前表面（21）的CMC壁（22）。 背部CMC表面（23）涂覆有导热材料层（42），以加速在CMC壁（22）的平面中的热传递，从而降低背面CMC表面（23）上的热梯度（32-40） ）由冲击冷却流产生的冷点（32）引起（26）。 导电材料（42）的导热系数可以比CMC材料（22）的导热系数高至少10倍，以提供最小厚度的导电层（42）。 这降低了CMC材料（22）内的热梯度应力，并且使CMC材料（22）和薄导电层（42）之间的差热膨胀应力最小化。

公开(公告)号：US07540711B2

公开(公告)日：2009-06-02

申请号：US11172929

申请日：2005-07-05

Applicant: Masahiko Arai ,  Hirotsugu Kawanaka ,  Kennichi Murata ,  Hideo Yoda

Inventor： Masahiko Arai ,  Hirotsugu Kawanaka ,  Kennichi Murata ,  Hideo Yoda

IPC: F04D29/04

CPC classification number: F01D5/02 ,  C22C38/02 ,  C22C38/04 ,  C22C38/44 ,  C22C38/46 ,  F01D5/28 ,  F05C2201/0466 ,  F05D2240/60 ,  F05D2300/131 ,  F05D2300/132 ,  F05D2300/161

Abstract: The invention provides a heat resisting steel having superior high-temperature strength and notch rupture strength, a rotor shaft using the heat resisting steel, a steam turbine using the rotor shaft, and a power plant using the steam turbine. The heat resisting steel is made of a Cr—Mo—V low-alloy steel containing 0.15-0.40% by weight of C, not more than 0.5% of Si, 0.05-0.50% of Mn, 0.5-1.5% of Ni, 0.8-1.5% of Cr, 0.8-1.8% of Mo and 0.05-0.35% of V, and having a (Ni/Mn) ratio of 3.0-10.0.

Abstract translation: 本发明提供一种具有优异的高温强度和切口断裂强度的耐热钢，使用该耐热钢的转子轴，使用该转子轴的蒸汽轮机，以及使用该蒸汽轮机的动力装置。 耐热钢由Cr-Mo-V低合金钢制成，含有0.15-0.40重量％的C，不超过0.5％的Si，0.05-0.50％的Mn，0.5-1.5％的Ni，0.8 -1.5％的Cr，0.8-1.8％的Mo和0.05-0.35％的V，并且（Ni / Mn）比为3.0-10.0。

公开(公告)号：US20090075101A1

公开(公告)日：2009-03-19

申请号：US12194577

申请日：2008-08-20

Applicant: Anand A. Kulkarni ,  Allister W. James ,  Douglas J. Arrell

Inventor： Anand A. Kulkarni ,  Allister W. James ,  Douglas J. Arrell

IPC: B32B15/00 ,  B32B15/04 ,  B32B15/01 ,  B05D1/02

CPC classification number: C23C30/00 ,  B22F1/0085 ,  B22F1/0088 ,  B22F9/082 ,  B22F2998/10 ,  B22F2999/00 ,  C22C1/002 ,  C23C4/073 ,  C23C4/10 ,  C23C24/04 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  C23C28/347 ,  F01D5/288 ,  F01D25/007 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/15 ,  Y10T428/12535 ,  Y10T428/12611 ,  Y10T428/1266 ,  Y10T428/31678 ,  B22F2201/01 ,  B22F2201/03 ,  C23C24/00

Abstract: A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes a first amount, by weight percent, of cobalt (Co) and a second amount, by weight percent, of nickel (Ni), the first amount being greater than the second amount. The alloy coating further includes chromium (Cr), aluminum (Al), at least one rare earth element, and an oxide of the at least one rare earth element.

Abstract translation: 燃气涡轮机部件（10）包括燃气轮机部件基板（16）和燃烧涡轮部件基板上的合金涂层（14）。 合金涂层（14）包括第一量的重量百分比的钴（Co）和第二量的以镍（Ni）的重量百分比计的第一量，第一量大于第二量。 合金涂层还包括铬（Cr），铝（Al），至少一种稀土元素和至少一种稀土元素的氧化物。

公开(公告)号：US20090074584A1

公开(公告)日：2009-03-19

申请号：US12210475

申请日：2008-09-15

Applicant: Kuniyoshi Nemoto ,  Kiyoshi Imai ,  Yomei Yoshioka ,  Masayuki Yamada ,  Reki Takaku ,  Takeo Suga ,  Masafumi Fukuda ,  Kenichi Okuno ,  Akihiro Takakuwa

Inventor： Kuniyoshi Nemoto ,  Kiyoshi Imai ,  Yomei Yoshioka ,  Masayuki Yamada ,  Reki Takaku ,  Takeo Suga ,  Masafumi Fukuda ,  Kenichi Okuno ,  Akihiro Takakuwa

IPC: B64C27/46 ,  C22C19/05

CPC classification number: C22C19/056 ,  C22C19/055 ,  F01D5/28 ,  F05C2201/0466 ,  F05D2220/31

Abstract: A Nickel-based alloy for a turbine rotor of a steam turbine contains C: 0.01 to 0.15, Cr: 18 to 28, Co: 10 to 15, Mo: 8 to 12, Al: 1.5 to 2, Ti: 0.1 to 0.6, B: 0.001 to 0.006, Ta: 0.1 to 0.7 in % by weight, and the remaining portion is composed of Ni and unavoidable impurities. The Nickel-based alloy is composed of the above-stated chemical composition range, and thereby, a mechanical strength improves while maintaining forgeability as same as a conventional steel.

Abstract translation: 用于汽轮机的涡轮转子的镍基合金含有C：0.01〜0.15，Cr：18〜28，Co：10〜15，Mo：8〜12，Al：1.5〜2，Ti：0.1〜0.6， B：0.001〜0.006，Ta：0.1〜0.7重量％，剩余部分由Ni和不可避免的杂质构成。 镍基合金由上述化学组成范围组成，从而与现有的钢一样保持锻造性，同时提高机械强度。

公开(公告)号：US20080263865A1

公开(公告)日：2008-10-30

申请号：US11916423

申请日：2006-06-23

Applicant: Bernd Daniels ,  Katrin Friedberger

Inventor： Bernd Daniels ,  Katrin Friedberger

IPC: B23P15/04 ,  B23K1/00

CPC classification number: F01D5/288 ,  B23K1/0018 ,  B23K2101/001 ,  F05C2201/0466 ,  F05C2203/0839 ,  Y10T29/49337

Abstract: A method for producing a blade tip armor plating on a blade of a turbomachine, in particular on a high-pressure compressor rotary blade of a gas turbine, having the following steps: a) provision of a blade made of a nickel base material; b) application of a solder to a blade tip of the blade, the solder being a nickel base solder; c) application of hard material particles of cubic boron nitride to the solder, the hard material particles of cubic boron nitride being coated with titanium or with a titanium base material; d) fusion of the solder in a vacuum in order to form a matrix that at least partially surrounds the hard material particles; and e) fixing of the blade tip armor plating through cooling.

Abstract translation: 一种用于在涡轮机的叶片上，特别是在燃气轮机的高压压缩机旋转叶片上生产叶片顶端装甲的方法，具有以下步骤：a）设置由镍基材料制成的叶片; b）将焊料施加到叶片的叶片尖端，焊料是镍基焊料; c）将立方氮化硼的硬质材料颗粒施加到焊料上，立方氮化硼的硬质材料颗粒用钛或钛基材料涂覆; d）在真空中熔化焊料，以形成至少部分地围绕硬质材料颗粒的基体; 和e）通过冷却来固定刀片护甲板。

公开(公告)号：US07435056B2

公开(公告)日：2008-10-14

申请号：US11413755

申请日：2006-04-28

Applicant: Laurence D. N. Liston

Inventor： Laurence D. N. Liston

IPC: F01D9/00

CPC classification number: F01D5/288 ,  F01D5/282 ,  F01D5/284 ,  F01D5/286 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/21 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/2263 ,  F05D2300/433 ,  F05D2300/603 ,  Y02T50/672

Abstract: The present invention provides a turbofan engine including leading edge erosion protection for composite stator vanes contained therein. The composite stator vanes are defined by a leading edge, a trailing edge, a concave surface and a convex surface. The vanes are generally formed of a graphite fiber and an aramid fiber braided preform that is laminated with an epoxy matrix resin or other high temperature matrix resin. A wire mesh screen is embedded during a molding process into an outermost surface of the leading edge of the epoxy matrix resin. A tapering erosion protection layer comprised of an erosion protective material is applied to the wire mesh screen at the leading edge of the composite stator vane an aids in protecting the leading edge of the stator vane from debris and contaminants, including operational fluids, dust, and sand that may be carried in an air stream passing therethrough the turbofan engine, as well as an erosive operational environment.

Abstract translation: 本发明提供一种涡轮风扇发动机，其包括其中包含的复合定子叶片的前缘侵蚀保护。 复合定子叶片由前缘，后缘，凹面和凸面限定。 叶片通常由石墨纤维和芳族聚酰胺纤维编织预制件形成，其与环氧树脂基质树脂或其它高温基质树脂层压。 在模制过程中将金属丝网屏蔽嵌入到环氧树脂基质树脂前缘的最外表面中。 由复合定子叶片的前缘将一个由侵蚀保护材料组成的锥形侵蚀保护层施加到丝网筛上，有助于保护定子叶片的前缘免受碎片和污染物的影响，包括操作流体，灰尘和 可能在通过涡轮风扇发动机的空气流中携带的沙子以及腐蚀性的操作环境。

公开(公告)号：US07311981B2

公开(公告)日：2007-12-25

申请号：US10974973

申请日：2004-10-28

Applicant: Bertrand Saint Ramond ,  Manuel Silva ,  John Nicholls ,  Maxime Carlin

Inventor： Bertrand Saint Ramond ,  Manuel Silva ,  John Nicholls ,  Maxime Carlin

IPC: B32B15/02 ,  B32B15/04 ,  B32B15/20 ,  F01D5/28

CPC classification number: C23C28/3455 ,  C23C14/00 ,  C23C16/00 ,  C23C28/322 ,  C23C28/325 ,  C23C28/345 ,  C23C28/42 ,  F01D5/288 ,  F05C2201/0466 ,  F05D2300/121 ,  F05D2300/143 ,  F05D2300/173 ,  Y10T428/12611 ,  Y10T428/12618 ,  Y10T428/12736 ,  Y10T428/1275 ,  Y10T428/12875 ,  Y10T428/12931 ,  Y10T428/12944 ,  Y10T428/263

Abstract: A gas turbine part comprises a superalloy metal substrate, a bonding underlayer formed on the substrate and comprising an intermetallic compound of aluminum, nickel, and platinum, and a ceramic outer layer anchored on the alumina film formed on the bonding underlayer. The bonding underlayer essentially comprises an Ni—Pt—Al ternary system constituted by an aluminum-enriched α-NiPt type structure, in particular an Ni—Pt—Al ternary system having a composition NizPtyAlx in which z, y, and x are such that 0.05≦z≦0.40, 0.30≦y≦0.60, and 0.15≦x≦0.40.

Abstract translation: 燃气轮机部分包括超合金金属基板，形成在基板上的包含铝，镍和铂的金属间化合物的接合底层和锚定在形成在粘合底层上的氧化铝膜上的陶瓷外层。 键合底层基本上包括由富铝的α-NiPt型结构构成的Ni-Pt-Al三元体系，特别是Ni-Pt-Al三元体系，其具有组成为Ni <！ - SIPO

公开(公告)号：US07300708B2

公开(公告)日：2007-11-27

申请号：US10801843

申请日：2004-03-16

Applicant: Michael Francis Xavier Gigliotti, Jr. ,  Canan Uslu Hardwicke ,  Liang Jiang ,  John William Short ,  Don Mark Lipkin ,  Jonathan Paul Blank ,  Krishnamurthy Anand

Inventor： Michael Francis Xavier Gigliotti, Jr. ,  Canan Uslu Hardwicke ,  Liang Jiang ,  John William Short ,  Don Mark Lipkin ,  Jonathan Paul Blank ,  Krishnamurthy Anand

IPC: B32B15/04 ,  B32B18/00

CPC classification number: B23K20/08 ,  F01D5/28 ,  F01D5/288 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2220/31 ,  F05D2230/311 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/501 ,  F05D2300/505 ,  F05D2300/611 ,  Y10S420/902 ,  Y10T428/12493 ,  Y10T428/12611 ,  Y10T428/12806 ,  Y10T428/12944

Abstract: An erosion resistant protective structure for a turbine engine component comprises a shape memory alloy. The shape memory alloy includes nickel-titanium based alloys, indium-titanium based alloys, nickel-aluminum based alloys, nickel-gallium based alloys, copper based alloys, gold-cadmium based alloys, iron-platinum based alloys, iron-palladium based alloys, silver-cadmium based alloys, indium-cadmium based alloys, manganese-copper based alloys, ruthenium-niobium based alloys, ruthenium-tantalum based alloys, titanium based alloys, iron-based alloys, or combinations comprising at least one of the foregoing alloys. Also, disclosed herein are methods for forming the shape memory alloy onto turbine component.

Abstract translation: 用于涡轮发动机部件的抗侵蚀保​​护结构包括形状记忆合金。 形状记忆合金包括镍 - 钛基合金，铟 - 钛基合金，镍 - 铝基合金，镍 - 镓基合金，铜基合金，金 - 镉基合金，铁 - 铂基合金，铁 - 钯基合金 银镉基合金，铟镉基合金，锰 - 铜基合金，钌 - 铌基合金，钌 - 钽基合金，钛基合金，铁基合金或包含至少一种上述合金的组合 。 此外，本文公开的是将形状记忆合金形成在涡轮部件上的方法。

公开(公告)号：US20070201984A1

公开(公告)日：2007-08-30

申请号：US11413755

申请日：2006-04-28

Applicant: Laurence Liston

Inventor： Laurence Liston

IPC: B63H1/26

CPC classification number: F01D5/288 ,  F01D5/282 ,  F01D5/284 ,  F01D5/286 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2300/21 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/2263 ,  F05D2300/433 ,  F05D2300/603 ,  Y02T50/672

Abstract: The present invention provides a turbofan engine including leading edge erosion protection for composite stator vanes contained therein. The composite stator vanes are defined by a leading edge, a trailing edge, a concave surface and a convex surface. The vanes are generally formed of a graphite fiber and an aramid fiber braided preform that is laminated with an epoxy matrix resin or other high temperature matrix resin. A wire mesh screen is embedded during a molding process into an outermost surface of the leading edge of the epoxy matrix resin. A tapering erosion protection layer comprised of an erosion protective material is applied to the wire mesh screen at the leading edge of the composite stator vane an aids in protecting the leading edge of the stator vane from debris and contaminants, including operational fluids, dust, and sand that may be carried in an air stream passing therethrough the turbofan engine, as well as an erosive operational environment.

Abstract translation: 本发明提供一种涡轮风扇发动机，其包括其中包含的复合定子叶片的前缘侵蚀保护。 复合定子叶片由前缘，后缘，凹面和凸面限定。 叶片通常由石墨纤维和芳族聚酰胺纤维编织预制件形成，其与环氧树脂基质树脂或其它高温基质树脂层压。 在模制过程中将金属丝网屏蔽嵌入到环氧树脂基质树脂前缘的最外表面中。 由复合定子叶片的前缘将一个由侵蚀保护材料组成的锥形侵蚀保护层施加到丝网筛上，有助于保护定子叶片的前缘免受碎片和污染物的影响，包括操作流体，灰尘和 可能在通过涡轮风扇发动机的空气流中携带的沙子以及腐蚀性的操作环境。