公开(公告)号：WO2014130158A1

公开(公告)日：2014-08-28

申请号：PCT/US2013/077964

申请日：2013-12-27

Applicant: KAPPES, Matthew J. ,  SCOTT, Matthew A. ,  WINFIELD, Chris J. ,  SCHNEIDER, Jared J.

Inventor： KAPPES, Matthew J. ,  SCOTT, Matthew A. ,  WINFIELD, Chris J. ,  SCHNEIDER, Jared J.

IPC: F01D21/04 ,  F01D11/12 ,  F02K3/06

CPC classification number: F01D21/045 ,  F01D11/122 ,  F02K3/06 ,  F05D2220/36 ,  Y02T50/672

Abstract: An embodiment of a gas turbine engine having a liner and casing is disclosed. The liner is disposed between the casing and a rotatable turbomachinery component. In one form, the rotatable turbomachinery component is a turbofan engine. The liner can be thin relative to a distance between the liner and the casing. Protrusions can be used between the liner and the casing. The protrusions can be a rib and can extend from the casing or the liner. An insert, such as an abradable surface, can be used with the liner. A filler can be used in the space between the liner and the casing. A corresponding method is also provided.

Abstract translation: 公开了具有衬套和壳体的燃气涡轮发动机的实施例。 衬套设置在壳体和可旋转的涡轮机械部件之间。 在一种形式中，可旋转的涡轮机组件是涡轮风扇发动机。 内衬可以相对于衬套和套管之间的距离较薄。 衬套和套管之间可以使用突起。 突起可以是肋，并且可以从壳体或衬垫延伸。 诸如可磨损表面的插入件可以与衬垫一起使用。 填料可以用在衬套和套管之间的空间中。 还提供了相应的方法。

公开(公告)号：WO2014165161A1

公开(公告)日：2014-10-09

申请号：PCT/US2014/024602

申请日：2014-03-12

Applicant: ROACH, John, M., III

Inventor： ROACH, John, M., III

IPC: F01D9/02 ,  F01D25/30 ,  F02C3/14

CPC classification number: F01D25/30 ,  F01D9/023 ,  F02C3/145 ,  Y10T137/0318 ,  Y10T137/0536

Abstract: A fluid plenum including a body defining an internal cavity having an inlet and an outlet. The fluid plenum further includes at least one wall positioned in the internal cavity that divides the internal cavity into first and second passageways, and which also divides the inlet into first and second inlet portions, and divides the outlet into first and second outlet portions. The first passageway receives fluid through the first inlet portion and directs fluid to the first outlet portion, and the second passageway receives fluid through the second inlet portion and directs fluid to the second outlet portion. The first and second passageways extend first and second lengths that are different from one another, and also generate a substantially common back-pressure at the first and second inlet portions during flow of a fluid stream through the inlet, including a first sub-stream of the fluid stream through the first passageway and a second sub-stream of the fluid stream through the second passageway.

Abstract translation: 流体增压室包括限定具有入口和出口的内部空腔的主体。 流体增压室还包括定位在内腔中的至少一个壁，其将内腔分成第一和第二通道，并且还将入口分成第一和第二入口部分，并将出口分成第一和第二出口部分。 第一通道通过第一入口部分接收流体并将流体引导到第一出口部分，并且第二通道接收通过第二入口部分的流体并将流体引导到第二出口部分。 第一和第二通道延伸彼此不同的第一和第二长度，并且还在流体流通过入口的流动期间在第一和第二入口部分处产生基本上常见的背压，包括第一和第二子流 通过第一通道的流体流和通过第二通道的流体流的第二子流。

公开(公告)号：WO2014163676A1

公开(公告)日：2014-10-09

申请号：PCT/US2013/072765

申请日：2013-12-03

Applicant: LAZUR, Andrew J. ,  FREEMAN, Ted J. ,  SIPPEL, Aaron D. ,  THOMAS, David J. ,  CHAMBERLAIN, Adam L. ,  LAMUSGA, Joseph P.

Inventor： LAZUR, Andrew J. ,  FREEMAN, Ted J. ,  SIPPEL, Aaron D. ,  THOMAS, David J. ,  CHAMBERLAIN, Adam L. ,  LAMUSGA, Joseph P.

IPC: F01D5/28 ,  B29C70/00

CPC classification number: F01D25/005 ,  B29C70/205 ,  F01D5/282 ,  F01D5/284 ,  F01D5/286 ,  Y02T50/672 ,  Y10T428/24025

Abstract: A composite component includes a bonded portion and a component mount. The component mount is coupled to the bonded portion to move relative to the bonded portion. The bonded portion includes a fiber portion and a ceramic portion.

Abstract translation: 复合部件包括接合部分和部件安装件。 部件安装件联接到接合部分以相对于接合部分移动。 接合部分包括纤维部分和陶瓷部分。

公开(公告)号：WO2014158240A2

公开(公告)日：2014-10-02

申请号：PCT/US2013/070922

申请日：2013-11-20

Applicant: ROLLS-ROYCE CORPORATION

Inventor： RAJASHEKARA, Kaushik ,  ROSS, Christine A. H. ,  ARMSTRONG, Michael ,  BLACKWELDER, Mark

IPC: B64D41/00

CPC classification number: B64D31/06 ,  B64C11/305 ,  B64D27/10 ,  B64D27/24 ,  B64D2027/026 ,  F01D7/02 ,  F01D15/10 ,  F01D21/00 ,  F02C7/32 ,  F02C9/20 ,  F02K1/18 ,  F05D2270/20 ,  F05D2270/304 ,  Y02T50/64 ,  Y02T50/677 ,  Y10S903/93

Abstract: A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.

Abstract translation: 用于混合涡轮增压电气航空推进系统的控制根据期望的优化目标对混合涡轮增压电动航空推进系统的多个不同控制优化子系统和跨越多个不同的控制优化子系统来优先考虑和优化运行参数。 控制子系统可以包括例如推进控制优化子系统和发电厂控制优化子系统。 优化可以基于在混合涡轮电动航空推进系统的操作期间开发和更新的系统模型。

公开(公告)号：WO2014149108A1

公开(公告)日：2014-09-25

申请号：PCT/US2013/076696

申请日：2013-12-19

Applicant: GRAVES, Charles B. ,  CUMMINGS, William, G., III ,  BENNETT, Russell N. ,  SHI, Jun

Inventor： GRAVES, Charles B. ,  CUMMINGS, William, G., III ,  BENNETT, Russell N. ,  SHI, Jun

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F05D2260/201 ,  F23R3/007 ,  F23R2900/00017 ,  Y10T29/49229

Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.

Abstract translation: 公开了一种适用于燃气涡轮发动机的燃烧器。 燃烧器包括形成空腔的金属壳和布置在金属壳的空腔中的陶瓷衬垫。 陶瓷衬套限定了在燃气涡轮发动机操作期间燃料燃烧的燃烧室。 陶瓷衬垫包括多个安装在金属壳上的陶瓷砖，并被布置成屏蔽金属壳体免受在燃烧室中产生的热量。

公开(公告)号：WO2014143248A1

公开(公告)日：2014-09-18

申请号：PCT/US2013/073985

申请日：2013-12-10

Applicant: VETTERS, Daniel, K. ,  KARAM, Michael ,  FULAYTER, Roy, D.

Inventor： VETTERS, Daniel, K. ,  FULAYTER, Roy, D.

IPC: F02K3/04 ,  F02C7/36

CPC classification number: F02K3/075 ,  F02C7/36 ,  F02K3/04 ,  F05D2260/4031 ,  Y02T50/671

Abstract: An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24.

Abstract translation: 超高旁通比涡扇发动机包括可变桨距风扇，低压涡轮机，减速齿轮箱和多个出口导叶。 超高旁路比涡扇发动机的旁通比约为18至40左右。变桨距风机和低压涡轮机通过减速齿轮箱联结在一起。 减速齿轮箱相对于低压涡轮机降低了变桨距风扇的速度。 多个出口导向叶片在可变节距风扇的后部间隔开并且被轴向扫掠。 可变节距风扇和低压涡轮机构造成产生约1.15至约1.24之间的风扇压力比。

公开(公告)号：WO2014137471A1

公开(公告)日：2014-09-12

申请号：PCT/US2013/078526

申请日：2013-12-31

Applicant: RIVERS, Jonathan, M. ,  FULAYTER, Roy, D.

Inventor： RIVERS, Jonathan, M. ,  FULAYTER, Roy, D.

IPC: B64D29/08

CPC classification number: F01D25/24 ,  B23P15/04 ,  B64D29/08 ,  B64D33/02 ,  B64D2033/0273 ,  F02C7/04 ,  F02K3/06 ,  Y10T29/49238

Abstract: An integrated access panel (62) is disclosed that can be used to assist in adjusting a component like a fan blade (64) of a turbofan engine. In one form the integrated access panel (62) is hinged at one end such that the panel remains attached during adjustment of the fan blade (64). The access panel (62) can be positioned in an angled flow surface of a nacelle such that the fan blade (64) cannot be removed from a wheel without removal of the nacelle or opening of the access panel (62). The integrated access panel (62) can be springloaded and positioned to allow the fan blade to be removed from a wheel by moving the access panel out of the way. Subsequent blade removal can occur by rotation of the wheel to locate another blade in proximity to the access panel.

Abstract translation: 公开了一种可用于协助调整涡扇发动机的风扇叶片（64）的组件的集成检修面板（62）。 在一种形式中，集成检修面板（62）在一端铰接，使得在调节风扇叶片（64）期间，面板保持附着。 检修面板（62）可以定位在机舱的倾斜的流动表面中，使得风扇叶片（64）不能从车轮上移除，而不拆卸机舱或打开接近面板（62）。 集成检修面板（62）可以被弹簧加载并定位成允许风扇叶片通过将检修面板移开而从轮子上移除。 随后的叶片移除可以通过轮的旋转而发生，以将另一个叶片定位在接近面板附近。

公开(公告)号：WO2014158277A2

公开(公告)日：2014-10-02

申请号：PCT/US2013/077893

申请日：2013-12-26

Applicant: FREEMAN, Ted J. ,  USKERT, Richard C.

Inventor： FREEMAN, Ted J. ,  USKERT, Richard C.

CPC classification number: F01D5/186 ,  B23P15/04 ,  F01D5/147 ,  F01D5/187 ,  F01D5/282 ,  F05D2230/10 ,  F05D2230/50 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2300/6033 ,  Y10T29/49337

Abstract: A method for making a gas turbine engine ceramic matrix composite airfoil is disclosed. The method includes fabricating an airfoil preform that has a slotted forward end and a continuous trailing end. The slotted forward end of the airfoil preform is coupled to an airfoil core insert. A ceramic matrix composite covering is applied to cover the slots of the airfoil perform. The continuous trailing end of the airfoil preform is removed to expose the slots. A gas turbine engine airfoil is also disclosed.

Abstract translation: 公开了一种制造燃气涡轮发动机陶瓷基复合材料翼型的方法。 该方法包括制造具有开槽前端和连续尾端的翼型件预制件。 翼型预成型件的开槽前端联接到翼型芯插入件。 涂覆陶瓷基质复合材料覆盖物以覆盖翼型件的槽。 翼型预制件的连续后端被移除以露出槽。 还公开了一种燃气涡轮发动机翼型。

公开(公告)号：WO2014143339A1

公开(公告)日：2014-09-18

申请号：PCT/US2013/077455

申请日：2013-12-23

Applicant: THOMAS, David, J. ,  FREEMAN, Ted, J. ,  USKERT, Richard, C. ,  JUNOD, Larry, A. ,  LAMUSGA, Joseph

Inventor： THOMAS, David, J. ,  FREEMAN, Ted, J. ,  USKERT, Richard, C. ,  JUNOD, Larry, A. ,  LAMUSGA, Joseph

IPC: F01D5/22 ,  F01D5/28

CPC classification number: F01D5/225 ,  F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F05D2300/6033 ,  Y02T50/672 ,  Y10T29/49321

Abstract: A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.

Abstract translation: 一种燃气涡轮发动机气流元件，其包括叶片芯部，从所述叶片芯部延伸的护罩前端部，以及形成在所述叶片芯部外侧的翼型部，所述叶片芯部和所述护罩前端部构成为第一 整体结构和翼型部分构造为第二结构。 还公开了一种形成燃气涡轮发动机部件的方法。

公开(公告)号：WO2014159178A1

公开(公告)日：2014-10-02

申请号：PCT/US2014/022389

申请日：2014-03-10

Applicant: LAZUR, Andrew, J. ,  CHAMBERLAIN, Adam, L.

Inventor： LAZUR, Andrew, J. ,  CHAMBERLAIN, Adam, L.

IPC: C04B35/573 ,  C04B35/628 ,  C04B35/80

CPC classification number: C04B35/806 ,  C04B35/573 ,  C04B35/6286 ,  C04B35/62863 ,  C04B35/62868 ,  C04B35/62873 ,  C04B35/62884 ,  C04B35/62894 ,  C04B35/62897 ,  C04B2235/3826 ,  C04B2235/421 ,  C04B2235/422 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/614 ,  C04B2235/616 ,  C23C16/045 ,  C23C16/32 ,  C23C16/325 ,  C23C16/342

Abstract: A method of producing a ceramic matrix composite comprising: a) applying a fiber interface coating to the composite, b) coating the composite via chemical vapor infiltration, and c) infiltrating the composite with molten material, wherein the composite is not removed from a tool between steps (a), (b), and (c), wherein the fiber interface coating and the chemical vapor infiltration are forced flow processes, wherein the forced flow fiber interface coating applies a pressure gradient of about 0.005 to about 1.0 atm, wherein the coating is carbon, boron nitride, or silicon doped boron nitride, wherein the chemical vapor infiltration applies silicon carbide, silicon nitride carbide, boron carbide, or carbon as a coating, wherein the coating is about 0.1 [micro]m to about 15.0 [micro]m, wherein the ceramic matrix composite is a tool, wherein the molten material comprises an alloy, wherein the molten material comprises silicon carbide, carbon, or a ceramic particulate, wherein the composite is multi-layered, wherein at least one layer comprises at least one of a carbide, a nitride, a boride, or carbon, for instance one layer is silicon carbide or boron nitride.

Abstract translation: 一种制备陶瓷基质复合材料的方法，包括：a）将纤维界面涂层施加到复合材料上，b）通过化学气相渗透涂覆复合材料，以及c）用熔融材料渗透复合材料，其中复合材料不被从工具中去除 在步骤（a），（b）和（c）之间，其中纤维界面涂层和化学气相渗透是强制流动过程，其中强制流动纤维界面涂层施加约0.005至约1.0atm的压力梯度，其中 涂层是碳，氮化硼或掺杂硅的氮化硼，其中化学气相渗透应用碳化硅，氮化碳，碳化硼或碳作为涂层，其中涂层为约0.1μm至约15.0μm， 其中所述陶瓷基质复合材料是工具，其中所述熔融材料包括合金，其中所述熔融材料包括碳化硅，碳或陶瓷颗粒，其中所述复合材料 是多层的，其中至少一层包括碳化物，氮化物，硼化物或碳中的至少一种，例如一层是碳化硅或氮化硼。