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公开(公告)号：JP2001304095A
公开(公告)日：2001-10-31
申请号：JP2001059797
申请日：2001-03-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： REY NANCY M , ROBIN MIHEKUN MILLER , TILLMAN THOMAS G , RUKUS ROBERT M , KETTLE JOHN L
Abstract: PROBLEM TO BE SOLVED: To increase force generated from an SMA material. SOLUTION: An SMA bundle 10 is formed of an individual SMA wire 12. This SMA bundle 10 has a base phase shape and a deformation shape, and outputs large force by returning to the base phase state by being heated in a deformation state. The SMA wire 12 for constituting the SMA bundle 10 can be constituted as a strand, a rope, a row or the other shape.
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公开(公告)号：JP2001289122A
公开(公告)日：2001-10-19
申请号：JP2001057733
申请日：2001-03-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： REY NANCY M , ROBIN MIHEKUN MILLER , TILLMAN THOMAS G , RUKUS ROBERT M , KETTLE JOHN L , DUNPHY JAMES R , CHAUDHRY ZAFFIR A , PEARSON DAVID D , DREITLEIN KENNETH C , LOFFREDO CONSTANTINO V , WYNOSKY THOMAS A
Abstract: PROBLEM TO BE SOLVED: To provide a gas turbine engine with a variable area nozzle requiring no large-scale maintenance without largely increasing the total weight of the gas turbine engine. SOLUTION: The gas turbine engine 10 includes a variable area nozzle 30 having a plurality of flaps 38. The flaps 38 are actuated by a plurality of actuating mechanisms 40 to be driven by a shape memory alloy(SMA) actuator 68. The SMA actuator 68 has a deformed shape in a martensitic state and a basic shape in an austenitic state. The SMA actuator 68 is heated to transform from the martensitic state into the austenitic state generating a force to actuate the flaps 38. The variable area nozzle 30 also contains a plurality of return mechanisms 42 for deforming the SMA actuator 68 when in the martensitic state.
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公开(公告)号：WO2014078467A3
公开(公告)日：2014-08-07
申请号：PCT/US2013069973
申请日：2013-11-14
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WORTH EDWIN M , TILLMAN THOMAS G , SCHWARZ FREDERICK M
IPC: B64C27/473 , F01D5/14 , F01D5/22
CPC classification number: F01D5/18 , F01D5/141 , F01D5/145 , F01D5/147 , F01D5/225 , F01D5/28 , F02C7/36 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2240/31 , F05D2250/181 , F05D2250/311 , F05D2250/321 , F05D2250/322 , F05D2250/62 , F05D2300/173 , F05D2300/174 , F05D2300/516 , Y02T50/672 , Y02T50/673 , Y10T29/49336
Abstract: A fan blade comprises a main body having an airfoil extending between a leading edge and a trailing edge. The fan blade has at least one of a channel closed by a cover, and an end cap covering at least one of the leading and trailing edges. At least one of a cover and an end cap has a pair of opposed ends. A step is defined extending from at least one of a suction wall and a pressure wall of the airfoil, to an outer surface of the one of a cover and an end cap at one of the opposed ends, and the step being less than or equal to about 0.010 inch (0.0254 centimeter) in dimension.
Abstract translation: 风扇叶片包括具有在前缘和后缘之间延伸的翼型件的主体。 风扇叶片具有由盖封闭的通道和覆盖前缘和后缘中的至少一个的端盖中的至少一个。 盖和端盖中的至少一个具有一对相对的端部。 从机翼的吸力壁和压力壁中的至少一个延伸到在相对端中的一个处的盖和端盖中的一个的外表面的步骤，并且该步骤小于或等于 到约0.010英寸（0.0254厘米）的尺寸。
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公开(公告)号：DE60112150D1
公开(公告)日：2005-09-01
申请号：DE60112150
申请日：2001-03-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： REY NANCY M , MILLER ROBIN MIHEKUN , TILLMAN THOMAS G , RUKUS ROBERT M , KETTLE JOHN L , DUNPHY JAMES R , CHAUDHRY ZAFFIR A , PEARSON DAVID D , DREITLEIN KENNETH C , LOFFREDO CONSTANTINO V , WYNOSKY THOMAS A
Abstract: A gas turbine engine (10) includes a variable area nozzle (30) having a plurality of flaps (38). The flaps (38) are actuated by a plurality of actuating mechanisms (40) driven by shape memory alloy (SMA) actuators (68) to vary fan exist nozzle area (36). The SMA actuator (68) has a deformed shape in its martensitic state and a parent shape in its austenitic state. The SMA actuator (68) is heated to transform from martensitic state to austenitic state generating a force output to actuate the flaps (38). The variable area nozzle (30) also includes a plurality of return mechanisms (42) deforming the SMA actuator (68) when the SMA actuator (68) is in its martensitic state.
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公开(公告)号：CA2568551A1
公开(公告)日：2007-07-18
申请号：CA2568551
申请日：2006-11-20
Applicant: UNITED TECHNOLOGIES CORP
Inventor： COFFIN CHARLES C , TILLMAN THOMAS G , WELCH BRIAN M , HUANG HE
Abstract: A fuel system for an energy conversion device includes a multiple of non- metallic fuel plates, gaskets, oxygen permeable membranes, porous substrate plates, and vacuum frame plates. Intricate 3-dimension fuel channel structures such as laminar flow impingement elements within the fuel channel dramatically enhan ce oxygen diffusivity in the FSU. The fuel plates are manufactured from a relatively soft non-metallic material. The non-metallic fuel plates and gasket arrangement provide an effective sealing interface between the fuel plate and oxygen permeable membrane, since compression may be applied to the plates without damaging th e relatively delicate oxygen permeable membrane.
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Patent Agency Ranking
公开(公告)号：CA2534158A1
公开(公告)日：2005-03-24
申请号：CA2534158
申请日：2004-09-08
Applicant: UNITED TECHNOLOGIES CORP
Inventor： KASLUSKY SCOTT F , TILLMAN THOMAS G , HUANG HE , DEVALVE TIMOTHY D , BERTUCCIOLI LUCA , LAMM FOSTER PHILIP , SPADACCINI LOUIS J , SABATINO DANIEL R , SAHM MICHAEL K , BAYT ROBERT L
IPC: B01D19/00 , C10L1/00 , B01D61/00 , B01D63/08 , B01D65/08 , B01D69/10 , B01D69/12 , B01D71/32 , B01D71/36 , F02C7/12 , F02C7/14 , F02C7/224
Abstract: A system (10) for the management of thermal transfer in a gas turbine engine (14) includes a heat generating sub-system disposed in operable communicatio n with the engine (14), a fuel source (18) configured to supply a fuel, a fuel stabilization unit (16) configured to receive the fuel from the fuel source (18) and to provide the fuel to the engine (14), and a heat exchanger dispos ed in thermal communication with the fuel to effect the transfer of heat from t he heat generating sub-system to the fuel. A method of managing such thermal transfer includes removing oxygen from the fuel in the fuel atabilization un it (16), transferring heat from the heat generating sub-system to the fuel, and combusting the fuel in gas turbine engine (14). System (10) can be used for the thermal management of an aircraft.
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公开(公告)号：DE60112150T2
公开(公告)日：2006-03-30
申请号：DE60112150
申请日：2001-03-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： REY NANCY M , MILLER ROBIN MIHEKUN , TILLMAN THOMAS G , RUKUS ROBERT M , KETTLE JOHN L , DUNPHY JAMES R , CHAUDHRY ZAFFIR A , PEARSON DAVID D , DREITLEIN KENNETH C , LOFFREDO CONSTANTINO V , WYNOSKY THOMAS A
Abstract: A gas turbine engine (10) includes a variable area nozzle (30) having a plurality of flaps (38). The flaps (38) are actuated by a plurality of actuating mechanisms (40) driven by shape memory alloy (SMA) actuators (68) to vary fan exist nozzle area (36). The SMA actuator (68) has a deformed shape in its martensitic state and a parent shape in its austenitic state. The SMA actuator (68) is heated to transform from martensitic state to austenitic state generating a force output to actuate the flaps (38). The variable area nozzle (30) also includes a plurality of return mechanisms (42) deforming the SMA actuator (68) when the SMA actuator (68) is in its martensitic state.
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公开(公告)号：DE60111095T2
公开(公告)日：2005-10-27
申请号：DE60111095
申请日：2001-03-02
Applicant: UNITED TECHNOLOGIES CORP HARTF
Inventor： REY NANCY M , RUKUS ROBERT M , MILLER ROBIN MIHEKUN , KETTLE JOHN L , TILLMAN THOMAS G
Abstract: A self contained shape memory alloy (SMA) mechanism (50) is presented comprising a first anchor (52) and a second anchor (54) with a SMA actuator (56) and a return member (58) disposed therebetween. The SMA actuator (56) is a SMA bundle formed of single wires. The return member (58) is a linear spring surrounding the SMA actuator (56). Each mechanism (50) also includes a heating means. In operation, with the SMA actuator (56) in a martensitic state, the spring (58) of the mechanism (50) stretches the SMA actuator (56). When the SMA actuator (56) is heated to achieve its austenitic state, the force of the SMA actuator overcomes the force of the spring and pulls the anchors (52,54) thereby actuating at least one of the anchors (52,54). One major benefit of the mechanisms (50) is the ability to repeatably generate high active force in a compact package.
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公开(公告)号：DE60111095D1
公开(公告)日：2005-07-07
申请号：DE60111095
申请日：2001-03-02
Applicant: UNITED TECHNOLOGIES CORP HARTF
Inventor： REY NANCY M , RUKUS ROBERT M , MILLER ROBIN MIHEKUN , KETTLE JOHN L , TILLMAN THOMAS G
Abstract: A self contained shape memory alloy (SMA) mechanism (50) is presented comprising a first anchor (52) and a second anchor (54) with a SMA actuator (56) and a return member (58) disposed therebetween. The SMA actuator (56) is a SMA bundle formed of single wires. The return member (58) is a linear spring surrounding the SMA actuator (56). Each mechanism (50) also includes a heating means. In operation, with the SMA actuator (56) in a martensitic state, the spring (58) of the mechanism (50) stretches the SMA actuator (56). When the SMA actuator (56) is heated to achieve its austenitic state, the force of the SMA actuator overcomes the force of the spring and pulls the anchors (52,54) thereby actuating at least one of the anchors (52,54). One major benefit of the mechanisms (50) is the ability to repeatably generate high active force in a compact package.
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公开(公告)号：EP3033497A4
公开(公告)日：2017-03-29
申请号：EP14836522
申请日：2014-04-17
Applicant: UNITED TECHNOLOGIES CORP
Inventor： FLOREA RAZVAN VIRGIL , TILLMAN THOMAS G , COUSINS WILLIAM T
IPC: F01D17/00 , B64C11/14 , F01D5/14 , F01D5/20 , F01D25/24 , F02C3/04 , F02C7/04 , F02C7/045 , F02K3/06 , F04D27/02 , F04D29/32 , F04D29/38 , F04D29/40 , F04D29/52 , F04D29/54
CPC classification number: F02K3/06 , F01D5/143 , F01D5/20 , F02C3/04 , F02C7/04 , F02C7/045 , F04D27/0246 , F04D29/321 , F04D29/526 , F04D29/547 , F05D2220/32 , F05D2220/36 , F05D2250/184 , F05D2250/25 , F05D2250/294 , F05D2250/61 , F05D2250/73 , F05D2270/102 , Y02T50/673
Abstract: A gas turbine engine propulsion system and method of assembling such is disclosed. The gas turbine engine propulsion system comprises a gas turbine engine that includes a fan flow path. The fan flow path may extend from the fan inlet to the rear exhaust outlet of the bypass flow path. A portion of the fan flow path, proximal to the fan, is non-axisymmetric. The non-axisymmetric portion may be upstream or downstream of the fan.
Abstract translation: 公开了一种燃气轮机发动机推进系统及其组装方法。 燃气涡轮发动机推进系统包括包括风扇流路的燃气涡轮发动机。 风扇流路可以从旁路流路的风扇入口延伸到后排气口。 靠近风扇的风扇流路的一部分是非轴对称的。 非轴对称部分可以在风扇的上游或下游。
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