Patents by Inventor Wayne S. Steffier

Wayne S. Steffier 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).

  • Patent number: 10941942
    Abstract: A combustor of a gas turbine engine and a turbine shroud for a turbine of a gas turbine engine are disclosed. The combustor is configured to ignite a mixture of compressed air and fuel in a combustion chamber included therein. The turbine shroud is configured to direct products of the combustion reaction toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: March 9, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Ted J. Freeman, Wayne S. Steffier
  • Patent number: 10577951
    Abstract: A gas turbine engine includes a turbine having turbine blades and a shroud having a blade track for positioning radially outside of the blades. At least one of the blades and the blade track are secured in place using a dovetail connection between a dovetail receiver and a dovetail assembly formed to include a contoured root.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: March 3, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Ted J. Freeman, Andrew J. Lazur, Robert J. Shinavski, Wayne S. Steffier
  • Publication number: 20200024955
    Abstract: A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.
    Type: Application
    Filed: November 27, 2018
    Publication date: January 23, 2020
    Inventors: Richard C. USKERT, David J. THOMAS, Wayne S. STEFFIER, Robert J. SHINAVSKI, Adam L. Chamberlain
  • Patent number: 10174619
    Abstract: A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.
    Type: Grant
    Filed: December 23, 2013
    Date of Patent: January 8, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Richard C. Uskert, David J. Thomas, Wayne S. Steffier, Robert J. Shinavski, Adam L. Chamberlain
  • Publication number: 20180149026
    Abstract: A gas turbine engine includes a turbine having turbine blades and a shroud having a blade track for positioning radially outside of the blades. At least one of the blades and the blade track are secured in place using a dovetail connection between a dovetail receiver and a dovetail assembly formed to include a contoured root.
    Type: Application
    Filed: November 30, 2016
    Publication date: May 31, 2018
    Inventors: Daniel K. Vetters, Ted J. Freeman, Andrew J. Lazur, Robert J. Shinavski, Wayne S. Steffier
  • Publication number: 20160186999
    Abstract: A combustor of a gas turbine engine and a turbine shroud for a turbine of a gas turbine engine are disclosed. The combustor is configured to ignite a mixture of compressed air and fuel in a combustion chamber included therein. The turbine shroud is configured to direct products of the combustion reaction toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate.
    Type: Application
    Filed: December 16, 2015
    Publication date: June 30, 2016
    Inventors: Ted J. Freeman, Wayne S. Steffier
  • Publication number: 20150003989
    Abstract: A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.
    Type: Application
    Filed: December 23, 2013
    Publication date: January 1, 2015
    Inventors: Richard C. Uskert, David J. Thomas, Wayne S. Steffier, Robert J. Shinavski, Adam L. Chamberlain
  • Patent number: 7988395
    Abstract: A relatively low cost, lightweight and thermal stress-free mechanical fastener system having particular application for reliably joining together high temperature structural members (e.g., a pair of flat fiber-reinforced ceramic composite plates). The mechanical fastener system includes a ceramic composite fastener having a semi-circular head at one end to be countersunk in the structural members to be joined together and a dove tail retention feature formed in the shank or root at the opposite end. The composite fastener has a 2-dimensional (i.e., flat) profile that facilitates an economic manufacture thereof from densified ceramic composite material. A matched pair of thread forms having external threads and an internal dove tail relief to match the dove tail retention feature at the root of the composite fastener is held in face-to-face mating engagement with one another so as to establish a mechanical interlock around the root of the composite fastener.
    Type: Grant
    Filed: January 23, 2009
    Date of Patent: August 2, 2011
    Inventor: Wayne S. Steffier
  • Publication number: 20100189529
    Abstract: A relatively low cost, lightweight and thermal stress-free mechanical fastener system having particular application for reliably joining together high temperature structural members (e.g., a pair of flat fiber-reinforced ceramic composite plates). The mechanical fastener system includes a ceramic composite fastener having a semi-circular head at one end to be countersunk in the structural members to be joined together and a dove tail retention feature formed in the shank or root at the opposite end. The composite fastener has a 2-dimensional (i.e., flat) profile that facilitates an economic manufacture thereof from densified ceramic composite material. A matched pair of thread forms having external threads and an internal dove tail relief to match the dove tail retention feature at the root of the composite fastener is held in face-to-face mating engagement with one another so as to establish a mechanical interlock around the root of the composite fastener.
    Type: Application
    Filed: January 23, 2009
    Publication date: July 29, 2010
    Inventor: Wayne S. Steffier
  • Patent number: 7479302
    Abstract: An actively-cooled, fiber-reinforced ceramic matrix composite thrust chamber for liquid rocket propulsion systems is designed and produced with internal cooling channels. The monocoque tubular structure consists of an inner wall, which is fully integrated to an outer wall via radial coupling webs. Segmented annular void spaces between the inner wall, outer wall and adjoining radial webs form the internal trapezoidal-shaped cooling channel passages of the tubular heat exchanger. The manufacturing method enables producing any general tubular shell geometry ranging from simple cylindrical heat exchanger tubes to complex converging-diverging, Delaval-type nozzle structures with an annular array of internal cooling channels. The manufacturing method allows for transitioning the tubular shell structure from a two-dimensional circular geometry to a three-dimensional rectangular geometry.
    Type: Grant
    Filed: June 14, 2004
    Date of Patent: January 20, 2009
    Inventor: Wayne S. Steffier
  • Patent number: 6979490
    Abstract: A fiber-reinforced ceramic matrix composite material exhibiting increased matrix cracking strength and fracture toughness is produced by sequentially depositing a plurality of 5-500 nanometer-thick layers of a primary ceramic matrix material phase periodically separated by 1-100 nanometer-thick intermediate layers of a secondary matrix material phase onto the reinforcing fibers upon their consolidation. The resultant nanolayered matrix enhances the resistance to the onset of matrix cracking, thus increasing the useful design strength of the ceramic matrix composite material. The nanolayered microstructure of the matrix constituent also provides a unique resistance to matrix crack propagation. Through extensive inter-layer matrix fracture, debonding and slip, internal matrix microcracks are effectively diverted and/or blunted prior to their approach towards the reinforcing fiber, thus increasing the apparent toughness of the matrix constituent.
    Type: Grant
    Filed: September 30, 2002
    Date of Patent: December 27, 2005
    Inventor: Wayne S. Steffier
  • Publication number: 20040222571
    Abstract: An actively-cooled, fiber-reinforced ceramic matrix composite thrust chamber for liquid rocket propulsion systems is designed and produced with internal cooling channels. The monocoque tubular structure consists of an inner wall, which is fully integrated to an outer wall via radial coupling webs. Segmented annular void spaces between the inner wall, outer wall and adjoining radial webs form the internal trapezoidal-shaped cooling channel passages of the tubular heat exchanger. The manufacturing method enables producing any general tubular shell geometry ranging from simple cylindrical heat exchanger tubes to complex converging-diverging, Delaval-type nozzle structures with an annular array of internal cooling channels. The manufacturing method allows for transitioning the tubular shell structure from a two-dimensional circular geometry to a three-dimensional rectangular geometry.
    Type: Application
    Filed: June 14, 2004
    Publication date: November 11, 2004
    Inventor: Wayne S. Steffier
  • Patent number: 6783824
    Abstract: An actively-cooled, fiber-reinforced ceramic matrix composite thrust chamber for liquid rocket propulsion systems is designed and produced with internal cooling channels. The monocoque tubular structure consists of an inner wall, which is fully integrated to an outer wall via radial coupling webs. Segmented annular void spaces between the inner wall, outer wall and adjoining radial webs form the internal trapezoidal-shaped cooling channel passages of the tubular heat exchanger. The manufacturing method enables producing any general tubular shell geometry ranging from simple cylindrical heat exchanger tubes to complex converging-diverging, Delaval-type nozzle structures with an annular array of internal cooling channels. The manufacturing method allows for transitioning the tubular shell structure from a two-dimensional circular geometry to a three-dimensional rectangular geometry.
    Type: Grant
    Filed: January 8, 2002
    Date of Patent: August 31, 2004
    Assignee: Hyper-Therm High-Temperature Composites, Inc.
    Inventor: Wayne S. Steffier
  • Publication number: 20030175453
    Abstract: An actively-cooled, fiber-reinforced ceramic matrix composite thrust chamber for liquid rocket propulsion systems is designed and produced with internal cooling channels. The monocoque tubular structure consists of an inner wall, which is fully integrated to an outer wall via radial coupling webs. Segmented annular void spaces between the inner wall, outer wall and adjoining radial webs form the internal trapezoidal-shaped cooling channel passages of the tubular heat exchanger. The manufacturing method enables producing any general tubular shell geometry ranging from simple cylindrical heat exchanger tubes to complex converging-diverging, Delaval-type nozzle structures with an annular array of internal cooling channels. The manufacturing method allows for transitioning the tubular shell structure from a two-dimensional circular geometry to a three-dimensional rectangular geometry.
    Type: Application
    Filed: January 8, 2002
    Publication date: September 18, 2003
    Inventor: Wayne S. Steffier
  • Patent number: 5558907
    Abstract: A fiber-reinforced ceramic composite material exhibiting high tensile strength, high fracture toughness and high-temperature oxidation resistance is produced by simultaneously depositing a thin coating layer of refractory metal carbide with fugitive carbon onto the fiber reinforcement prior to the subsequent densification with the ceramic matrix. The energy behind propagating matrix cracks in the resulting composite material are effectively dissipated by crack deflection/branching, fiber debonding and frictional slip through the relatively weak and compliant fiber coating layer. These energy release and arrest mechanisms sufficiently impede the driving force behind unstable crack propagation and render the cracks non-critical, thereby serving to blunt and/or divert propagating matrix cracks at or around the reinforcing fiber.
    Type: Grant
    Filed: September 8, 1995
    Date of Patent: September 24, 1996
    Assignee: Hyper-Therm High Temperature Composites, Inc.
    Inventor: Wayne S. Steffier
  • Patent number: 5545435
    Abstract: A fiber-reinforced ceramic-matrix composite material exhibiting high tensile strength, high fracture toughness and high-temperature oxidation resistance is produced by alternatively depositing multiple thin layers of ceramic material separated by very thin intermediate layers of fugitive carbon onto the fiber reinforcement prior to the subsequent densification with the ceramic matrix. The energy behind propagating matrix cracks in the resulting composite material are effectively dissipated by the progressive increase in crack deflection/branching and frictional slip through the successive ceramic layers of the multilayer fiber coating system. These energy release and arrest mechanisms sufficiently impede the driving force behind unstable crack propagation and render the cracks non-critical, thereby serving to blunt and/or divert propagating matrix cracks at or around the reinforcing fiber.
    Type: Grant
    Filed: September 8, 1995
    Date of Patent: August 13, 1996
    Assignee: Hyper-Therm High Temperature Composites, Inc.
    Inventor: Wayne S. Steffier
  • Patent number: 5480707
    Abstract: A fiber reinforced ceramic composite material exhibiting high tensile strength, high fracture toughness and high-temperature oxidation resistance is produced by simultaneously depositing a thin coating layer of refractory metal carbide with fugitive carbon onto the fiber reinforcement prior to the subsequent densification with the ceramic matrix. The energy behind propagating matrix cracks in the resulting composite material are effectively dissipated by crack deflection/branching, fiber debonding and frictional slip through the relatively weak and compliant fiber coating layer. These energy release and arrest mechanisms sufficiently impede the driving force behind unstable crack propagation and render the cracks non-critical, thereby serving to blunt and/or divert propagating matrix cracks at or around the reinforcing fiber.
    Type: Grant
    Filed: October 6, 1993
    Date of Patent: January 2, 1996
    Assignee: Hyper-Thern High-Temperature Composites, Inc.
    Inventor: Wayne S. Steffier
  • Patent number: 5455106
    Abstract: A fiber-reinforced ceramic-matrix composite material exhibiting high tensile strength, high fracture toughness and high-temperature oxidation resistance is produced by alternatively depositing multiple thin layers of ceramic material separated by very thin intermediate layers of fugitive carbon onto the fiber reinforcement prior to the subsequent densification with the ceramic matrix. The energy behind propagating matrix cracks in the resulting composite material are effectively dissipated by the progressive increase in crack deflection/branching and frictional slip through the successive ceramic layers of the multilayer fiber coating system. These energy release and arrest mechanisms sufficiently impede the driving force behind unstable crack propagation and render the cracks non-critical, thereby serving to blunt and/or divert propagating matrix cracks at or around the reinforcing fiber.
    Type: Grant
    Filed: October 6, 1993
    Date of Patent: October 3, 1995
    Assignee: Hyper-Therm High Temperature Composites, Inc.
    Inventor: Wayne S. Steffier
  • Patent number: 5337974
    Abstract: An aircraft wing pivot structure is described which provides a flexible ring attached to the aircraft wing at flexible wing attachment points by spherical bearings. The ring is attached to the fuselage of the aircraft by pins fixed to the fuselage and fittings partially enclosing sliding shoes formed at the bottom edge of the ring to allow rotation of the wing. The wing is locked in the flight position by retractable pins connected to the primary fuselage attachment fittings. The ring is a unitary stainless structure which accepts wing strains induced by flight loads by flexing at the wing attachment points. The use of a flexible ring eliminates truss-like members mounted on spherical bearings used in conventional designs. The elimination of a substantial number of components by the use of a flexible ring substantially reduces the weight of the aircraft and improves the reliability.
    Type: Grant
    Filed: April 15, 1992
    Date of Patent: August 16, 1994
    Assignee: The Boeing Company
    Inventors: William E. Rumberger, Wayne S. Steffier
  • Patent number: 5221578
    Abstract: A ceramic fiber/ceramic matrix composite has ceramic fibers and a porous coating on the fibers. A ceramic matrix contacts the porous coating, the fiber and coating being immersed in the ceramic matrix. The porous coating is selected from the group including Si.sub.3 N.sub.4, SiC, ZrO.sub.2, Al.sub.2 O.sub.3, SnO.sub.2 and Ta.sub.2 O.sub.5. The pores are generally empty so as to render the coating frangible to promote fiber de-bonding and pull-out in the wake of an advancing crack in the matrix. In order to keep the pores empty, a non-porous sealing layer is formed over the porous coating which closes the pores without filling them. The ceramic matrix remains generally outside of the pores, whereby said pores remain empty after the fiber and coating are immersed in the ceramic matrix.
    Type: Grant
    Filed: March 13, 1991
    Date of Patent: June 22, 1993
    Assignee: Northrop Corporation
    Inventors: Harry W. Carpenter, James W. Bohlen, Wayne S. Steffier