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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：AT156569T
公开(公告)日：1997-08-15
申请号：AT92914392
申请日：1992-04-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WYNOSKY THOMAS A , MISCHKE ROBERT J
IPC: F02K1/38
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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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Patent Agency Ranking
公开(公告)号：CA1091453A
公开(公告)日：1980-12-16
申请号：CA291382
申请日：1977-11-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WYNOSKY THOMAS A , STREIB RICHARD A , CAMPBELL CHARLES A
Abstract: LOBE MIXER FOR GAS TURBINE ENGINE The lobe-type mixer on a turbine type power plant is improved upon by "scalloping" the side walls for enhancing mixing of two flow streams to obtain improved noise suppression and/or engine performance. The improved lobed mixer also minimizes pressure losses.
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公开(公告)号：DE60134347D1
公开(公告)日：2008-07-17
申请号：DE60134347
申请日：2001-03-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： REY NANCY M , DUNPHY JAMES R , MILLER ROBIN MIHEKUN , CHAUDRY ZAFFIR A , TILMAN THOMAS G , PEARSON DAVID D , RUKUS ROBERT M , DREITLEIN KENNETH C , KETTLE JOHN L , LOFFREDO CONSTANTINTO , 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：CA1145568A
公开(公告)日：1983-05-03
申请号：CA362128
申请日：1980-10-10
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WYNOSKY THOMAS A , EILER DONALD C , BLATT JERROLD R
Abstract: LOBED MIXER/INVERTER A fairing added to the upstream end of the lobe of conventional lobed mixers or inverters for a gas turbine engine redirects the boundary layer so as to improve engine performance. EH-7136
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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：CA1257971A
公开(公告)日：1989-08-01
申请号：CA532736
申请日：1987-03-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： WYNOSKY THOMAS A
Abstract: Gas Turbine Engine Nacelle A nacelle structure (14) for a gas turbine engine (4) extends upstream from the engine air inlet (10) and includes an external surface (18) and an internal surface (16). The external surface (18) is concentric about a linear centerline (22) which is disposed parallel to the free airflow stream (6) encountered by the nacelle (14) in flight. The internal surface (16) is concentric about a curved centerline (30), the curved centerline (30) being parallel to the free airflow stream (6) at the nacelle inlet (12) and parallel to the engine centerline (26) at the engine air inlet (10) for smoothly directing the internal airflow stream (32) into the engine air inlet (10).
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