Patents by Inventor Rajendra Agrawal

Rajendra Agrawal 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: 7334983
    Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.
    Type: Grant
    Filed: October 27, 2005
    Date of Patent: February 26, 2008
    Assignee: United Technologies Corporation
    Inventors: Ioannis Alvanos, Rajendra Agrawal, Gregory E. Reinhardt
  • Publication number: 20070098545
    Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.
    Type: Application
    Filed: October 27, 2005
    Publication date: May 3, 2007
    Inventors: Ioannis Alvanos, Rajendra Agrawal, Gregory Reinhardt
  • Publication number: 20070059158
    Abstract: A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing means restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing means restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing means and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.
    Type: Application
    Filed: September 12, 2005
    Publication date: March 15, 2007
    Inventors: Ioannis Alvanos, Rajendra Agrawal, Hector Pinero
  • Publication number: 20060275107
    Abstract: Disclosed are assemblies and articles for restricting leakage of a pressurized fluid from a cavity. In accordance with an embodiment of the invention, a vane support defines at least one land, and an interrupted rim region of a bladed rotor assembly defines at least one segmented ring. The at least one segmented ring protruding outward from the bladed rotor assembly in the interrupted rim region, spans across the cavity and cooperates with the at least one land to define a seal.
    Type: Application
    Filed: June 7, 2005
    Publication date: December 7, 2006
    Inventors: Ioannis Alvanos, Rajendra Agrawal, John Virtue, James Hill, Hector Pinero
  • Publication number: 20060275106
    Abstract: Disclosed are assemblies and articles for restricting leakage of a pressurized fluid from a cavity. In accordance with an embodiment of the invention, a vane support defines a land, and a neck region of a bladed rotor assembly defines a segmented ring. The segmented ring protrudes outward from the bladed rotor assembly in the neck region, spans across the cavity and cooperates with the land to define a seal.
    Type: Application
    Filed: June 7, 2005
    Publication date: December 7, 2006
    Inventors: Ioannis Alvanos, Rajendra Agrawal
  • Patent number: 7114339
    Abstract: A gas turbine engine having a turbine section cooling system is disclosed which is able to cool the turbine section of the gas turbine engine to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils, turning holes, and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section in a direction in substantial alignment with a gas flow path through the turbine section.
    Type: Grant
    Filed: March 30, 2004
    Date of Patent: October 3, 2006
    Assignee: United Technologies Corporation
    Inventors: Ioannis Alvanos, Rajendra Agrawal, Hector M. Pinero, Jin Hu
  • Publication number: 20050217277
    Abstract: A gas turbine engine having a turbine section cooling system is disclosed which is able to cool the turbine section of the gas turbine engine to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils, turning holes, and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section in a direction in substantial alignment with a gas flow path through the turbine section.
    Type: Application
    Filed: March 30, 2004
    Publication date: October 6, 2005
    Inventors: Ioannis Alvanos, Rajendra Agrawal, Hector Pinero, Jin Hu