Patents by Inventor Sami Girgis

Sami Girgis 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).

  • LP turbine vane airfoil profile
    Patent number: 7367779
    Abstract: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: March 2, 2006
    Date of Patent: May 6, 2008
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sami Girgis, Panagiota Tsifourdaris
  • LP turbine blade airfoil profile
    Patent number: 7354249
    Abstract: A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: March 2, 2006
    Date of Patent: April 8, 2008
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sami Girgis, Krishan Mohan
  • HP turbine vane airfoil profile
    Patent number: 7351038
    Abstract: A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: March 2, 2006
    Date of Patent: April 1, 2008
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sami Girgis, Krishan Mohan, Mona El-Fouly
  • HP turbine blade airfoil profile
    Publication number: 20080063530
    Abstract: A first stage blade of a two-stage high pressure turbine includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: September 7, 2006
    Publication date: March 13, 2008
    Inventors: Michael Papple, Edward Vlasic, Sami Girgis
  • HP turbine blade airfoil profile
    Publication number: 20080063531
    Abstract: A second stage blade of a two-stage high pressure turbine includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: September 7, 2006
    Publication date: March 13, 2008
    Inventors: Sri Sreekanth, Edward Vlasic, Sami Girgis
  • HP Turbine Vane Airfoil Profile
    Publication number: 20080056896
    Abstract: A two-stage high pressure turbine includes a first stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: September 6, 2006
    Publication date: March 6, 2008
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Ricardo Trindade, Edward Vlasic, Sami Girgis
  • LP turbine blade airfoil profile
    Publication number: 20080056903
    Abstract: A single stage low pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: September 5, 2006
    Publication date: March 6, 2008
    Inventors: Sami Girgis, Krishan Mohan
  • HP turbine vane airfoil profile
    Publication number: 20080056893
    Abstract: A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: September 5, 2006
    Publication date: March 6, 2008
    Inventors: Remo Marini, Sami Girgis
  • Turbine exhaust strut airfoil and gas path profile
    Publication number: 20080056901
    Abstract: A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: September 5, 2006
    Publication date: March 6, 2008
    Inventors: Stephen Mah, Sami Girgis
  • HP turbine blade airfoil profile
    Publication number: 20080056902
    Abstract: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: September 5, 2006
    Publication date: March 6, 2008
    Inventors: Constantinos Ravanis, Sami Girgis, Krishan Mohan
  • LP turbine vane airfoil profile
    Publication number: 20080056894
    Abstract: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: September 5, 2006
    Publication date: March 6, 2008
    Inventors: Panagiota Tsifourdaris, Sami Girgis
  • HP turbine blade airfoil profile
    Patent number: 7306436
    Abstract: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: March 2, 2006
    Date of Patent: December 11, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sami Girgis, Constantinos Ravanis
  • LP turbine vane airfoil profile
    Publication number: 20070207037
    Abstract: A single stage low pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: March 2, 2006
    Publication date: September 6, 2007
    Inventors: Sami Girgis, Panagiota Tsifourdaris
  • HP turbine blade airfoil profile
    Publication number: 20070207035
    Abstract: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: March 2, 2006
    Publication date: September 6, 2007
    Inventors: Sami Girgis, Constantinos Ravanis
  • HP turbine vane airfoil profile
    Publication number: 20070207036
    Abstract: A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: March 2, 2006
    Publication date: September 6, 2007
    Inventors: Sami Girgis, Krishan Mohan, Mona El-Fouly
  • Turbine exhaust strut airfoil profile
    Publication number: 20070207038
    Abstract: A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Application
    Filed: March 2, 2006
    Publication date: September 6, 2007
    Inventors: Sami Girgis, Krishan Mohan, Mona El-Fouly
  • Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
    Patent number: 7244104
    Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
    Type: Grant
    Filed: May 31, 2005
    Date of Patent: July 17, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sami Girgis, Remo Marini
  • Blade and disk radial pre-swirlers
    Patent number: 7189056
    Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
    Type: Grant
    Filed: May 31, 2005
    Date of Patent: March 13, 2007
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Sami Girgis, Remo Marini
  • Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
    Publication number: 20060269399
    Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
    Type: Application
    Filed: May 31, 2005
    Publication date: November 30, 2006
    Inventors: Sami Girgis, Remo Marini
  • Blade and disk radial pre-swirlers
    Publication number: 20060269400
    Abstract: A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.
    Type: Application
    Filed: May 31, 2005
    Publication date: November 30, 2006
    Inventors: Sami Girgis, Romo Marini