Patents by Inventor Mark A. Stephens

Mark A. Stephens 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).

  • Publication number: 20200173463
    Abstract: A compressor airfoil of a turbine engine that has a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
    Type: Application
    Filed: October 29, 2019
    Publication date: June 4, 2020
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Publication number: 20200149545
    Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is provided in the compressor section outside the high pressure compressor section and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle has a positive slope from 20% span to 100% span.
    Type: Application
    Filed: January 14, 2020
    Publication date: May 14, 2020
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Publication number: 20200149546
    Abstract: A compressor airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction. A positive sweep angle is in the rearward direction. The airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is negative at 0% span and changes less than 10° from 0% span to 90% span.
    Type: Application
    Filed: October 2, 2019
    Publication date: May 14, 2020
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Publication number: 20200149544
    Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span. The camber angle is less than 20° within the entire range of 40% span to 100% span.
    Type: Application
    Filed: January 13, 2020
    Publication date: May 14, 2020
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Publication number: 20200124053
    Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.
    Type: Application
    Filed: December 20, 2019
    Publication date: April 23, 2020
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10605259
    Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with a leading edge angle of less than 40° at 100% span.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: March 31, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Publication number: 20200096005
    Abstract: A gas turbine engine includes a combustor section, a compressor section, and a turbine section. A high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. A low pressure compressor is counter-rotating relative to the fan blades and downstream from the fan section. The airfoil outside of the compressor section is rotatable relative to an engine static structure. The airfoil includes pressure and suction sides extending from a 0% span position to a 100% span position. A relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span. The leading edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the leading edge.
    Type: Application
    Filed: November 12, 2019
    Publication date: March 26, 2020
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10590775
    Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 32° from 90% span to 100% span.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10584715
    Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 35° from 0% span to at least 50% span.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: March 10, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10570915
    Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle from 80% span to 100% span.
    Type: Grant
    Filed: February 16, 2015
    Date of Patent: February 25, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10570916
    Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.
    Type: Grant
    Filed: February 16, 2015
    Date of Patent: February 25, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10557477
    Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.
    Type: Grant
    Filed: February 16, 2015
    Date of Patent: February 11, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10530114
    Abstract: The disclosed subject matter relates to a polarization-maintaining very large mode area (PM VLMA) Erbium-doped fiber and a polarization maintaining, Er-doped VLMA amplifier.
    Type: Grant
    Filed: August 31, 2017
    Date of Patent: January 7, 2020
    Assignee: United States of America as represented by the Administrator of NASA
    Inventors: Mark A. Stephen, Anthony W. Yu, Jeffrey W. Nicholson
  • Patent number: 10516246
    Abstract: The present invention is related to laser technology which enables efficient, passive, coherent beam combination from distributed gain sources. The present invention includes a novel architecture which coherently combines the power from multiple sources, and which adds considerable flexibility to laser gain materials for many applications. The novel architecture of the present invention combines two techniques: 1) beam splitting and combination; and 2) phase-locking (i.e., maintaining a common phase relationship between multiple beams), using reflective gratings. Thus, the present invention addresses important limitations in laser technology: efficiency, power scaling and wavelength selectivity.
    Type: Grant
    Filed: August 24, 2017
    Date of Patent: December 24, 2019
    Assignee: United States of America as represented by the Administrator of NASA
    Inventor: Mark A. Stephen
  • Patent number: 10502229
    Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: December 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10495106
    Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
    Type: Grant
    Filed: February 17, 2015
    Date of Patent: December 3, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10465702
    Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction, and a positive sweep angle is in the rearward direction.
    Type: Grant
    Filed: February 17, 2015
    Date of Patent: November 5, 2019
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10352331
    Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: July 16, 2019
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Publication number: 20190067894
    Abstract: The present invention is related to laser technology which enables efficient, passive, coherent beam combination from distributed gain sources. The present invention includes a novel architecture which coherently combines the power from multiple sources, and which adds considerable flexibility to laser gain materials for many applications. The novel architecture of the present invention combines two techniques: 1) beam splitting and combination; and 2) phase-locking (i.e., maintaining a common phase relationship between multiple beams), using reflective gratings. Thus, the present invention addresses important limitations in laser technology: efficiency, power scaling and wavelength selectivity.
    Type: Application
    Filed: August 24, 2017
    Publication date: February 28, 2019
    Inventor: MARK A. STEPHEN
  • Publication number: 20190067895
    Abstract: The disclosed subject matter relates to a polarization-maintaining very large mode area (PM VLMA) Erbium-doped fiber and a polarization maintaining, Er-doped VLMA amplifier.
    Type: Application
    Filed: August 31, 2017
    Publication date: February 28, 2019
    Inventors: MARK A. STEPHEN, ANTHONY W. YU, JEFFREY W. NICHOLSON