Patents by Inventor Joseph C. Straccia

Joseph C. Straccia 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).

  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20170175760
    Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge dihedral angle and span position defined by a curve with the leading edge dihedral angle including 10° or less change from 0% span to 60% span.
    Type: Application
    Filed: February 17, 2015
    Publication date: June 22, 2017
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20170175758
    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: Application
    Filed: February 12, 2015
    Publication date: June 22, 2017
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20170167503
    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: Application
    Filed: February 12, 2015
    Publication date: June 15, 2017
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20170167266
    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: Application
    Filed: February 12, 2015
    Publication date: June 15, 2017
    Applicant: United Technologies Corporation
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20170167267
    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 leading edge position and span position that defines a curve with a negative slope from 90% span to 100% span. The negative slope corresponds to a forward leaning leading edge.
    Type: Application
    Filed: February 17, 2015
    Publication date: June 15, 2017
    Applicant: United Technologies Corporation
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20170159670
    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: Application
    Filed: February 16, 2015
    Publication date: June 8, 2017
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Gas turbine engine airfoil
    Patent number: 9567858
    Abstract: An airfoil of a turbine engine according to an example of the present disclosure includes, among other things, 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 a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
    Type: Grant
    Filed: February 19, 2015
    Date of Patent: February 14, 2017
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160363128
    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: Application
    Filed: February 12, 2015
    Publication date: December 15, 2016
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160356285
    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: Application
    Filed: February 16, 2015
    Publication date: December 8, 2016
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160348691
    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: Application
    Filed: February 12, 2015
    Publication date: December 1, 2016
    Applicant: United Technologies Corporation
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160341213
    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: Application
    Filed: February 17, 2015
    Publication date: November 24, 2016
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160341217
    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: Application
    Filed: February 17, 2015
    Publication date: November 24, 2016
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160341211
    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: February 16, 2015
    Publication date: November 24, 2016
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160131151
    Abstract: An airfoil arrangement of a turbine engine according to an example of the present disclosure includes adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
    Type: Application
    Filed: January 15, 2016
    Publication date: May 12, 2016
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • INCIDENCE-TOLERANT, HIGH-TURNING FAN EXIT STATOR
    Publication number: 20160076380
    Abstract: A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.
    Type: Application
    Filed: August 14, 2015
    Publication date: March 17, 2016
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel K. Van Ness, Mark A. Stephens, Edward J. Gallagher, Joseph C. Straccia, Vikram A. Kumar
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160069187
    Abstract: An airfoil of a turbine engine according to an example of the present disclosure includes, among other things, 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 a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope.
    Type: Application
    Filed: February 19, 2015
    Publication date: March 10, 2016
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20150233250
    Abstract: An airfoil of a turbine engine includes, pressure and suction sides extending in a radial direction from a 0% span to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio of less than 0.80 from 80% span to 100% span.
    Type: Application
    Filed: February 17, 2015
    Publication date: August 20, 2015
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • HIGH ORDER SHAPED CURVE REGION FOR AN AIRFOIL
    Publication number: 20150198045
    Abstract: A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region.
    Type: Application
    Filed: March 26, 2015
    Publication date: July 16, 2015
    Inventor: Joseph C. Straccia
  • High order shaped curve region for an airfoil
    Patent number: 9017036
    Abstract: A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: April 28, 2015
    Assignee: United Technologies Corporation
    Inventor: Joseph C. Straccia
  • HIGH ORDER SHAPED CURVE REGION FOR AN AIRFOIL
    Publication number: 20130224040
    Abstract: A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region.
    Type: Application
    Filed: April 24, 2012
    Publication date: August 29, 2013
    Inventor: Joseph C. Straccia