Patents by Inventor Lyle D. Dailey
Lyle D. Dailey 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: 11959393Abstract: An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.Type: GrantFiled: November 10, 2021Date of Patent: April 16, 2024Assignees: General Electric Company, GE Avivo S.r.l.Inventors: Saurya Ranjan Ray, Francesco Bertini, Lyle Douglas Dailey, Jeffrey D. Clements, Jaikumar Loganathan, Simone Rosa Taddei
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Patent number: 11125089Abstract: A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.Type: GrantFiled: August 7, 2019Date of Patent: September 21, 2021Assignees: General Electric Company, GE Avio S.r.l.Inventors: Francesco Bertini, Aspi Rustom Wadia, Lyle D. Dailey, Andrea Arnone, Filippo Rubechini, Matteo Giovannini, Paul Hadley Vitt, Jeffrey Donald Clements
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Publication number: 20200362713Abstract: A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.Type: ApplicationFiled: August 7, 2019Publication date: November 19, 2020Inventors: Francesco Bertini, Aspi Rustom Wadia, Lyle D. Dailey, Andrea Arnone, Filippo Rubechinni, Matteo Giovanni, Paul Hadley Vitt, Jeffrey Donald Clements
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Patent number: 8517677Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.Type: GrantFiled: May 31, 2012Date of Patent: August 27, 2013Assignee: General Electric CompanyInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Patent number: 8292574Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.Type: GrantFiled: November 30, 2006Date of Patent: October 23, 2012Assignee: General Electric CompanyInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Publication number: 20120237344Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.Type: ApplicationFiled: May 31, 2012Publication date: September 20, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Patent number: 8087884Abstract: A stator vane includes leading and trailing edges extending longitudinally between a root and a tip, the trailing edge having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location.Type: GrantFiled: November 30, 2006Date of Patent: January 3, 2012Assignee: General Electric CompanyInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Patent number: 7967571Abstract: A rotor airfoil having a leading edge extending from a root to a tip, an inner span region and an outer span region the leading edge having a sweep angle profile such that the sweep angle increases from the root a first height location at a first rate of change of sweep angle that is substantially constant and thereafter increases at a second rate of change of sweep angle that is substantially constant.Type: GrantFiled: November 30, 2006Date of Patent: June 28, 2011Assignee: General Electric CompanyInventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Publication number: 20100260609Abstract: A rotor airfoil having a leading edge extending from a root to a tip, an inner span region and an outer span region the leading edge having a sweep angle profile such that the sweep angle increases from the root a first height location at a first rate of change of sweep angle that is substantially constant and thereafter increases at a second rate of change of sweep angle that is substantially constant.Type: ApplicationFiled: November 30, 2006Publication date: October 14, 2010Inventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Publication number: 20080131271Abstract: A stator vane includes leading and trailing edges extending longitudinally between a root and a tip, the trailing edge having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location.Type: ApplicationFiled: November 30, 2006Publication date: June 5, 2008Inventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey
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Publication number: 20080131272Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.Type: ApplicationFiled: November 30, 2006Publication date: June 5, 2008Inventors: Peter John Wood, Eric Andrew Falk, Lyle D. Dailey