Patents by Inventor Charles M. Evans
Charles M. Evans 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: 9945232Abstract: A gas turbine engine blade (22), including an airfoil substrate (10) having an exterior surface, wherein: a base (14) of the airfoil substrate is located at a 0% radial on an inner platform surface (20) and a tip (16) of the airfoil substrate is located at a 100% radial; wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1; and wherein at a 50% radial location a cross-sectional profile of the exterior surface is characterized by nominal X and Y coordinates present in Table 6.Type: GrantFiled: May 12, 2014Date of Patent: April 17, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Eric Munoz, Edwin Lee Kite, Robert J. McClelland, Charles M. Evans
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Patent number: 9903210Abstract: A turbine blade tip shroud (22C, 22D) with a seal rail (32C, 32D) oriented in a circumferential direction of rotation (29) relative to a turbine axis, and extending radially outward from the tip relative to the turbine axis. A first tooth (48, 68) and a second tooth (50, 70) form respective downstream and upstream lateral departures or bumps on the seal rail. Each tooth has a sharp top leading edge (48, 50, 68, 70) and a smoothly curved side surface (49, 51, 69, 71). A back portion (56, 76) of the seal rail may span linearly from a lateral peak (66, 78) of the second tooth to a back end (62) of the seal rail that is centered on an extended centerline (60) of a front portion (54, 74) of the seal rail. The teeth may be disposed proximate or over a stacking axis (52) of the blade.Type: GrantFiled: May 20, 2014Date of Patent: February 27, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Charles M. Evans, Andrew R. Narcus, John Pula
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Patent number: 9828858Abstract: A turbine blade airfoil (25, 31R, 31M, 31T, 72) comprising an outer surface shape defined by Cartesian coordinates of successive transverse profiles at radial increments as set forth in Tables 1a to 1k, wherein each table defines a transverse sectional profile characterized by a smooth curve connecting the coordinates, and the surface shape comprises a smooth surface connecting the sectional profiles. The blade may include a tip shroud with edge profiles defined by Cartesian coordinates set forth in Table 2a and 2b. A gusset/fillet may be provided between the blade airfoil and the tip shroud, with a planar diagonal surface over most of a diagonal bracing area of the gusset/fillet.Type: GrantFiled: May 20, 2014Date of Patent: November 28, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Eric Munoz, Edwin Lee Kite, John Pula, Charles M. Evans
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Publication number: 20160115795Abstract: A turbine blade airfoil (25, 31R, 31M, 31T, 72) comprising an outer surface shape defined by Cartesian coordinates of successive transverse profiles at radial increments as set forth in Tables 1a to 1k, wherein each table defines a transverse sectional profile characterized by a smooth curve connecting the coordinates, and the surface shape comprises a smooth surface connecting the sectional profiles. The blade may include a tip shroud with edge profiles defined by Cartesian coordinates set forth in Table 2a and 2b. A gusset/fillet may be provided between the blade airfoil and the tip shroud, with a planar diagonal surface over most of a diagonal bracing area of the gusset/fillet.Type: ApplicationFiled: May 20, 2014Publication date: April 28, 2016Applicant: Siemens Energy, Inc.Inventors: Eric Munoz, Edwin Lee Kite, John Pula, Charles M. Evans
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Publication number: 20160108749Abstract: A turbine blade tip shroud (22C, 22D) with a seal rail (32C, 32D) oriented in a circumferential direction of rotation (29) relative to a turbine axis, and extending radially outward from the tip relative to the turbine axis. A first tooth (48, 68) and a second tooth (50, 70) form respective downstream and upstream lateral departures or bumps on the seal rail. Each tooth has a sharp top leading edge (48, 50, 68, 70) and a smoothly curved side surface (49, 51, 69, 71). A back portion (56, 76) of the seal rail may span linearly from a lateral peak (66, 78) of the second tooth to a back end (62) of the seal rail that is centered on an extended centerline (60) of a front portion (54, 74) of the seal rail. The teeth may be disposed proximate or over a stacking axis (52) of the blade.Type: ApplicationFiled: May 20, 2014Publication date: April 21, 2016Applicant: Siemens Energy, Inc.Inventors: Charles M. EVANS, Andrew R. NARCUS, John PULA
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Publication number: 20160102558Abstract: A gas turbine engine blade (22), including an airfoil substrate (10) having an exterior surface, wherein: a base (14) of the airfoil substrate is located at a 0% radial on an inner platform surface (20) and a tip (16) of the airfoil substrate is located at a 100% radial; wherein at the 0% radial a cross-sectional profile of the exterior surface is substantially characterized by nominal X and Y coordinates present in Table 1; and wherein at a 50% radial location a cross-sectional profile of the exterior surface is characterized by nominal X and Y coordinates present in Table 6.Type: ApplicationFiled: May 12, 2014Publication date: April 14, 2016Applicant: Siemens Energy, Inc.Inventors: Eric Munoz, Edwin Lee Kite, Robert J. McClelland, Charles M. Evans
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Publication number: 20160102562Abstract: A gas turbine engine blade (10), having: an airfoil (12) having a pressure side (22) and a suction side (24); an inner platform (30), having: a gas path surface (40); a coolant surface (42); and at least one row (114) of film cooling holes (112) spanning there between and disposed on the pressure side of the airfoil. The film cooling holes are angled to include a directional component substantially parallel with the pressure side at a trailing end of the airfoil, and the at least one row is oriented substantially parallel to a mateface wall (122) of the inner platform. An array (130) of turbulators (132) is disposed on the coolant surface.Type: ApplicationFiled: May 20, 2014Publication date: April 14, 2016Applicant: Siemens Energy, Inc.Inventors: Charles M. Evans, Andrew R. Narcus, Robert J. McClelland, Frank Moehrle
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Publication number: 20160084088Abstract: A gas turbine engine blade (10) having: an airfoil (12) having a leading edge (14), a trailing edge (16), a pressure side (22), and a suction side (24); an inner platform (30) associated with a base (18) of the airfoil, wherein the inner platform includes a platform aft face (34) spanning between an platform pressure side face (36) and a platform suction side face (38); and a trailing edge undercut (70) across the aft face. The trailing edge undercut tapers to zero penetration before reaching the platform suction side face. In a side cross section, a leading portion (100) of the trailing edge undercut is defined by a leading radius (102), an upper portion (104) is defined by an upper radius (106), and a lower portion (108) is defined by a lower radius (110). For at least one location along the aft face, values for all three radii are distinct.Type: ApplicationFiled: May 20, 2014Publication date: March 24, 2016Applicant: SIEMENS ENERGY, INC.Inventors: Charles M. Evans, Andrew R. Narcus