Patents by Inventor Kevin Kirtley
Kevin Kirtley 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: 8289279Abstract: The present invention provides a wireless keyboard system for a digital computer. The keyboard system further comprises a housing having a keyboard section, function key section, and numeric key section cooperatively arranged on the top surface area of the housing. The keyboard section has keys for generating key signals. The keys of the keyboard section are substantially arranged in a standard QWERTY or DVORAK typewriting key format. The function key section has keys configured to generate application or system specific key signals. The numeric key section has keys configured to generate numeric key signals. The keyboard system further comprises a switch configured to switch the numeric key section between a keyboard mode and a calculator mode. A small display is operationally mounted on the top surface of the housing near the numeric key section. The display is operational within the calculator mode.Type: GrantFiled: October 8, 2004Date of Patent: October 16, 2012Inventors: Donny Kevin Kirtley, Pamela Kay Kirtley
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Patent number: 7678165Abstract: A particle separator which broadly includes: an inner wall, an outer wall and a splitter, wherein the inner and outer walls define an air intake passageway, and wherein the splitter is positioned between the inner and outer walls so as to define a scavenge air flow passageway connected to the intake passageway and a main air flow passageway connected to the intake passageway; the inner wall having a humped-shaped portion between the intake passageway and the main air flow passageway; the humped-shaped portion having a peak and a radius of curvature at any point on the hump-shaped portion of the inner wall after the peak corresponding to a degree of curvature of from about 30 to about 60 degrees; and a boundary layer control mechanism for providing active boundary layer control along the inner wall after the peak and within the main air flow passageway. Also provided is a method for providing active boundary layer flow control along the inner wall after the peak and within the main air flow passageway.Type: GrantFiled: December 28, 2006Date of Patent: March 16, 2010Assignee: General Electric CompanyInventors: Walter Jackson Tingle, Wayne R. Oliver, Kevin Kirtley
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Patent number: 7581692Abstract: A system for jet engine noise control of a jet engine having a main jet stream exiting an exhaust nozzle and flowing along a jet axis includes a thermal acoustic shield directed at a non-zero angle relative to the jet axis. The thermal acoustic shield may be configurable about the main jet stream. The system may further include at least a fluidic chevron injected at a location relative to the nozzle exit for enhancing mixing in the main jet stream and creating a non-circular jet stream.Type: GrantFiled: June 30, 2003Date of Patent: September 1, 2009Assignee: General Electric CompanyInventors: Paolo Graziosi, Kevin Kirtley, Ramani Mani
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Patent number: 7463242Abstract: The present invention comprises a stationary wireless mouse for a computer system. The wireless mouse further comprises a casing defined by an upper surface, a left side, fight side, and a flat bottom surface area. The upper surface area further includes a raised crown portion dimension to accommodate the palm region of the hand. The upper surface area also includes a front section and a back section. Extending forward from the crown portion is the front section of the casing. Extending backward from the crown portion is the back section of the casing. A navigation stick is configured to generate precise on-screen cursor control movement key signals. The navigation stick is positioned in the upper left comer of the forward section of the casing for operation by the index finger. For a predetermined short distance, the navigation stick extends vertically upward a slight distance above the top surface area.Type: GrantFiled: October 8, 2004Date of Patent: December 9, 2008Inventors: Donny Kevin Kirtley, Pamela Kay Kirtley
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Publication number: 20070147987Abstract: A flow control system for a centrifugal compressor includes a plurality of suction holes provided in a diffuser and configured to facilitate suction of a flow control stream from a boundary layer fluid from the diffuser. A plurality of blowing holes are provided in a first interconnecting duct coupled to a de-swirl vane unit and configured to facilitate blowing of the flow control stream into the first interconnecting duct. The blowing holes may also be provided in a suction side or an end wall side of the de-swirl vane unit or in a second interconnecting duct coupled between the de-swirl vane unit and an impeller or an upstream diffuser of another compression stage. A manifold is coupled between the suction holes and the blowing holes and configured to direct flow of the flow control stream from the suction holes to the blowing holes.Type: ApplicationFiled: December 22, 2005Publication date: June 28, 2007Inventor: Kevin Kirtley
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Publication number: 20070089422Abstract: A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the at least two injection openings is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation. Methods for optimizing the flow through the turbine engine are also disclosed.Type: ApplicationFiled: October 25, 2005Publication date: April 26, 2007Inventors: James Widenhoefer, Paolo Graziosi, Kevin Kirtley
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Publication number: 20060233641Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform includes a crescentic ramp increasing in height from the leading and trailing edges toward the midchord of the airfoil along the pressure side thereof.Type: ApplicationFiled: April 14, 2005Publication date: October 19, 2006Inventors: Ching-Pang Lee, Anna Tam, Kevin Kirtley, Scott Lamson
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Publication number: 20060228208Abstract: An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port.Type: ApplicationFiled: December 19, 2005Publication date: October 12, 2006Inventors: Richard Trewin, Jason Mortzheim, Edip Sevincer, Kevin Kirtley, Roointon Pavri, Xiaoyue Liu
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Publication number: 20060140768Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a bulge adjoining the pressure side adjacent the leading edge, and a bowl adjoining the suction side aft of the leading edge.Type: ApplicationFiled: December 24, 2004Publication date: June 29, 2006Inventors: Anna Tam, Ching-Pang Lee, Kevin Kirtley, Ronald Bunker, Scott Lamson, Scott Carson
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Publication number: 20060067821Abstract: An airfoil having a root, a tip, and an outer surface for pressuring air flowable thereover. The outer surface includes one or more slots elongate in a direction selected to preclude or reduce circulation within the slots, and the one or more slots are configured to bleed a boundary layer from the outer surface to the tip utilizing one or more passageways within the airfoil.Type: ApplicationFiled: September 28, 2004Publication date: March 30, 2006Inventors: Aspi Wadia, Peter Szucs, Syed Khalid, Peter Wood, Kevin Kirtley, Xiaoyue Liu
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Publication number: 20050279100Abstract: A bypass channel for use in an inter-turbine transition duct of a gas turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and an injection port disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the injection nozzle is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation.Type: ApplicationFiled: June 18, 2004Publication date: December 22, 2005Inventors: Paolo Graziosi, Kevin Kirtley
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Publication number: 20050100438Abstract: An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port.Type: ApplicationFiled: November 10, 2003Publication date: May 12, 2005Applicant: GENERAL ELECTRIC COMPANYInventors: Richard Trewin, Jason Mortzheim, Edip Sevincer, Kevin Kirtley, Roointon Pavri, Xiaoyue Liu
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Patent number: 6851264Abstract: In various embodiments, the present invention provides a means for improving gas turbine engine performance by applying fluid flow control to the inter-turbine duct joining a high-pressure turbine spool and an associated low-pressure turbine spool, allowing the low-pressure turbine spool to have a relatively larger diameter than the high-pressure turbine spool. One or more unobstructed fluid flow paths between one or more boundary layer suction ports disposed within the upstream end of the outer-body surface of the inter-turbine duct and the suction side of the associated low-pressure turbine nozzle are provided. Advantageously, the natural static pressure difference between these points results in a self-aspirating assembly. The fluid flow control provided by the respective suction and blowing forces generated allows for a relatively larger diameter low-pressure turbine spool and/or relatively fewer low-pressure turbine nozzles to be used than is possible with conventional systems, assemblies, and methods.Type: GrantFiled: October 24, 2002Date of Patent: February 8, 2005Assignee: General Electric CompanyInventors: Kevin Kirtley, Paolo Graziosi
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Publication number: 20040262447Abstract: A system for jet engine noise control of a jet engine having a main jet stream exiting an exhaust nozzle and flowing along a jet axis includes a thermal acoustic shield directed at a non-zero angle relative to the jet axis. The thermal acoustic shield may be configurable about the main jet stream. The system may further include at least a fluidic chevron injected at a location relative to the nozzle exit for enhancing mixing in the main jet stream and creating a non-circular jet stream.Type: ApplicationFiled: June 30, 2003Publication date: December 30, 2004Inventors: Paolo Graziosi, Kevin Kirtley, Ramani Mani
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Publication number: 20040079084Abstract: In various embodiments, the present invention provides a means for improving gas turbine engine performance by applying fluid flow control to the inter-turbine duct joining a high-pressure turbine spool and an associated low-pressure turbine spool, allowing the low-pressure turbine spool to have a relatively larger diameter than the high-pressure turbine spool. One or more unobstructed fluid flow paths between one or more boundary layer suction ports disposed within the upstream end of the outer-body surface of the inter-turbine duct and the suction side of the associated low-pressure turbine nozzle are provided. Advantageously, the natural static pressure difference between these points results in a self-aspirating assembly. The fluid flow control provided by the respective suction and blowing forces generated allows for a relatively larger diameter low-pressure turbine spool and/or relatively fewer low-pressure turbine nozzles to be used than is possible with conventional systems, assemblies, and methods.Type: ApplicationFiled: October 24, 2002Publication date: April 29, 2004Inventors: Kevin Kirtley, Paolo Graziosi