×

CONTINUOUS DETONATION GAS TURBINE ENGINE

  • US 20190017437A1
  • Filed: 07/13/2017
  • Published: 01/17/2019
  • Est. Priority Date: 07/13/2017
  • Status: Abandoned Application
First Claim
Patent Images

1. A gas turbine engine comprising:

  • a primary combustor including an annular combustion chamber extending between front and rear ends of the primary combustor;

    a high pressure (HP) turbine downstream of the primary combustor and fluidly connected to the rear end of the primary combustor via a first exhaust duct, the first exhaust duct positioned to direct a primary exhaust stream emitted from the primary combustor to the HP turbine;

    a secondary combustor including an annular combustion chamber extending between front and rear ends of the secondary combustor; and

    a mixing duct disposed downstream of the HP turbine and the secondary combustor, the mixing duct having a first inlet fluidly connected to the HP turbine via a turbine exit duct, a second inlet fluidly connected to the rear end of the secondary combustor via a second exhaust duct, and an outlet, wherein the turbine exit duct directs the primary exhaust stream from the HP turbine into the mixing duct and the second exhaust duct directs a secondary exhaust stream emitted from the secondary combustor into the mixing duct.

View all claims
  • 1 Assignment
Timeline View
Assignment View
    ×
    ×