Patents by Inventor Francois CASTEILLA

Francois CASTEILLA 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).

  • Method for manufacturing a two-component blade for a gas turbine engine and blade obtained by such a method
    Patent number: 10486230
    Abstract: A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.
    Type: Grant
    Filed: June 29, 2015
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Francois Casteilla, Sebastien Digard Brou De Cuissart, Serge Alain Fargeas, Vincent Marc Herb, Chantal Sylvette Marie-Noël Langlois
  • METHOD FOR MANUFACTURING A TWO-COMPONENT BLADE FOR A GAS TURBINE ENGINE AND BLADE OBTAINED BY SUCH A METHOD
    Publication number: 20170136534
    Abstract: A method of fabricating a two-component blade for a gas turbine engine, the method including in succession: obtaining a blade profile made of ceramic material having a hole passing right through the blade profile in its length direction so as to form a longitudinal channel opening out into a top cavity; positioning and maintaining the blade profile in a mold so as to form a bottom cavity communicating with the channel of the blade profile; casting molten metal into the blade profile so as to fill the top and bottom cavities and the channel interconnecting them; and cooling the metal so that the shrinkage of the metal cooled in the top and bottom cavities leads to the ceramic of the blade profile being subjected to compression prestress.
    Type: Application
    Filed: June 29, 2015
    Publication date: May 18, 2017
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Francois CASTEILLA, Sebastien DIGARD BROU DE CUISSART, Serge FARGEAS, Vincent HERB