Patents by Inventor Michael J. Larkin
Michael J. Larkin has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11933789Abstract: A device includes: a first portion configured to be grasped by the hand of the user, and a second portion defining a reservoir containing a control material, wherein the control material contains a target analyte in a known or predetermined concentration. A method of verifying the accuracy of an analyte monitoring device includes receiving a fluid sample, identifying the fluid sample as a control solution, and analyzing the fluid sample.Type: GrantFiled: May 5, 2021Date of Patent: March 19, 2024Assignee: Intuity Medical, Inc.Inventors: Kelley J. Lipman, Michael F. Tomasco, Peter Uy-Vu Ly, Jennifer Y. Blomo, Paul D. Reynolds, John F. Larkin, Robin S. Gaffney, Kimberly J. Tansey, Christopher L. Stewart, Raul Escutia, Robert W. Bowers
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Patent number: 8844294Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly that includes an inlet lip section and an inlet internal diffuser section downstream of the inlet lip section. A variable area fan nozzle is positioned near an aft segment of the nacelle assembly, the variable area fan nozzle adaptable to move between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area. At least one boundary layer control device is positioned near one of the inlet lip section and the inlet internal diffuser section. A controller is configured to move the variable area fan nozzle from the first position to the second position and to actuate the at least one boundary layer control device to introduce an airflow in response to an operability condition.Type: GrantFiled: April 9, 2014Date of Patent: September 30, 2014Assignee: United Technologies CorporationInventors: Stephen A. Morford, Michael J. Larkin
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Publication number: 20140216002Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly that includes an inlet lip section and an inlet internal diffuser section downstream of the inlet lip section. A variable area fan nozzle is positioned near an aft segment of the nacelle assembly, the variable area fan nozzle adaptable to move between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area. At least one boundary layer control device is positioned near one of the inlet lip section and the inlet internal diffuser section. A controller is configured to move the variable area fan nozzle from the first position to the second position and to actuate the at least one boundary layer control device to introduce an airflow in response to an operability condition.Type: ApplicationFiled: April 9, 2014Publication date: August 7, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Stephen A. Morford, Michael J. Larkin
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Patent number: 8726632Abstract: A method of providing a slim-line nacelle for a gas turbine engine includes the steps of detecting a windmilling condition and increasing a discharge airflow area of a variable area fan nozzle in response to the detection of the windmilling condition.Type: GrantFiled: July 8, 2010Date of Patent: May 20, 2014Assignee: United Technologies CorporationInventors: Stephen A. Morford, Michael J. Larkin
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Patent number: 8353164Abstract: A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section, and a variable area fan nozzle moveable to influence a discharge airflow area of the nacelle. The first boundary layer control device is positioned near the inlet lip section and is actuable to introduce a first airflow at the inlet lip section. The second boundary layer control device is positioned near the inlet internal diffuser section and is actuable to introduce a second airflow at the inlet internal diffuser section. The sensor produces a signal that represents an operability condition.Type: GrantFiled: July 8, 2010Date of Patent: January 15, 2013Assignee: United Technologies CorporationInventors: Stephen A. Morford, Michael J. Larkin
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Publication number: 20100269512Abstract: A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section, and a variable area fan nozzle moveable to influence a discharge airflow area of the nacelle. The first boundary layer control device is positioned near the inlet lip section and is actuable to introduce a first airflow at the inlet lip section. The second boundary layer control device is positioned near the inlet internal diffuser section and is actuable to introduce a second airflow at the inlet internal diffuser section. The sensor produces a signal that represents an operability condition.Type: ApplicationFiled: July 8, 2010Publication date: October 28, 2010Inventors: Stephen A. Morford, Michael J. Larkin
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Publication number: 20100269486Abstract: A method of providing a slim-line nacelle for a gas turbine engine includes the steps of detecting a windmilling condition and increasing a discharge airflow area of a variable area fan nozzle in response to the detection of the windmilling condition.Type: ApplicationFiled: July 8, 2010Publication date: October 28, 2010Inventors: Stephen A. Morford, Michael J. Larkin
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Patent number: 7797944Abstract: A nacelle assembly for a gas turbine engine includes a nacelle, a variable area fan nozzle, a sensor that detects a windmilling condition and a controller that communicates with the sensor. The variable area fan nozzle is moveable between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area in response to detecting the windmilling condition.Type: GrantFiled: October 20, 2006Date of Patent: September 21, 2010Assignee: United Technologies CorporationInventors: Stephen A. Morford, Michael J. Larkin
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Patent number: 7454894Abstract: A gas turbine engine is provided with an oil cooler which receives cooling air from a turbo fan. At times when the turbo fan is operating at lower speeds, the volume of cooling air is also lowered. At such times, a supplemental airflow is provided over heat exchangers in the oil cooler. The supplemental airflow includes a supplemental airflow fan and valve for selectively controlling the supplemental airflow over the heat exchangers.Type: GrantFiled: December 7, 2004Date of Patent: November 25, 2008Assignee: United Technologies CorporationInventors: Michael J. Larkin, Donald C. Eiler
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Publication number: 20080092548Abstract: A nacelle assembly for a gas turbine engine includes a nacelle, a variable area fan nozzle, a sensor that detects a windmilling condition and a controller that communicates with the sensor. The variable area fan nozzle is moveable between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area in response to detecting the windmilling condition.Type: ApplicationFiled: October 20, 2006Publication date: April 24, 2008Inventors: Stephen A. Morford, Michael J. Larkin
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Patent number: 6837038Abstract: The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engine to the turbine for driving the turbine and the fan and thereby generating additional thrust for the aircraft. The engine is also used to provide power to one or more systems onboard the aircraft.Type: GrantFiled: October 15, 2002Date of Patent: January 4, 2005Assignee: United Technologies CorporationInventors: Donald C. Eiler, Michael J. Larkin
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Publication number: 20030070418Abstract: The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engine to the turbine for driving the turbine and the fan and thereby generating additional thrust for the aircraft. The engine is also used to provide power to one or more systems onboard the aircraft.Type: ApplicationFiled: October 15, 2002Publication date: April 17, 2003Inventors: Donald C. Eiler, Michael J. Larkin
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Patent number: 5689999Abstract: Apparatus for enabling and disabling relative rotary movements between two members rotatable about a common axis comprises a plurality of circumferentially spaced locking pins carried by one of the members and a plurality of circumferentially spaced sockets in the other of the members, the pins and sockets being uniformly spaced from the axis of rotation and each of the sockets being of such size as to accommodate any one of the pins. The number of pins is different from the number of sockets. The angular spacing between adjacent pins is uniform, and the angular spacing between adjacent sockets is uniform, but different from the angular spacing between adjacent pins. The angular spacing between the pins and the sockets defines a ratio which is not a whole integer.Type: GrantFiled: August 18, 1995Date of Patent: November 25, 1997Assignee: Gunnell, Inc.Inventors: Robert A. Wiley, Dwight S. Gay, Michael J. Larkin
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Patent number: 4864820Abstract: An exhaust nozzle extends from an engine nacelle and has an opening disposed at an acute angle such that the exhaust stream is blown over a length of the propeller blade. The opening has a plurality of guide vanes disposed therein to shape the exhaust stream most effectively. By spreading the exhaust stream over the length of a propeller, mixing of the exhaust stream with ambient air is maximized, thereby lowering the temperature of the exhaust stream to tolerable levels.Type: GrantFiled: October 22, 1987Date of Patent: September 12, 1989Assignee: United Technologies CorporationInventors: Thomas A. Wynosky, Michael J. Larkin, William E. Fortmann