CONTINUOUS DETONATION GAS TURBINE ENGINE
First Claim
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.
1 Assignment
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Accused Products
Abstract
A gas turbine engine includes a primary combustor, a secondary combustor, a high pressure (HP) turbine, and a mixing duct. The HP turbine is downstream of the primary combustor and fluidly connected to a rear end of the primary combustor via a first exhaust duct. The mixing duct is disposed downstream of the HP turbine and the secondary combustor. The mixing duct has a first inlet fluidly connected to the HP turbine via a turbine exit duct, a second inlet fluidly connected to a rear end of the secondary combustor via a second exhaust duct, and an outlet. The turbine exit duct directs a primary exhaust stream, which is emitted from the primary combustor and expanded through the HP turbine, into the mixing duct. The second exhaust duct directs a secondary exhaust stream emitted from the secondary combustor into the mixing duct.
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Citations
20 Claims
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1. A gas turbine engine comprising:
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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 Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A method comprising:
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providing a compressor upstream of a primary combustor that has an annular combustion chamber extending between front and rear ends of the primary combustor, the compressor fluidly connected to the front end of the primary combustor via a primary air duct positioned to direct a first compressed air stream from the compressor to the primary combustor; providing 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; providing a secondary combustor downstream of the compressor, the secondary combustor having an annular combustion chamber extending between front and rear ends of the secondary combustor, the front end of the secondary combustor fluidly connected to the compressor via a bleed duct positioned to direct a second compressed air stream from the compressor to the secondary combustor; and providing a mixing duct downstream of both the HP turbine and the secondary combustor, the mixing duct including 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. - View Dependent Claims (12, 13, 14, 15, 16)
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17. A gas turbine engine comprising:
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a primary combustor and a secondary combustor, each of the primary and secondary combustors including a respective annular combustion chamber extending between front and rear ends of the respective primary and secondary combustors; a compressor disposed upstream of the primary and secondary combustors, the compressor extending between an inlet end and an outlet end and includes multiple stages of rotor blades and stator vanes distributed in a high pressure section and a lower pressure section, the low pressure section disposed upstream of the high pressure section between the inlet end and the high pressure section, the compressor fluidly connected to the front end of the primary combustor via a primary air duct configured to direct a first compressed air stream to the primary combustor, the compressor fluidly connected to the front end of the secondary combustor via a bleed duct configured to direct a different, second compressed air stream to the secondary 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; 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 into the mixing duct and the second exhaust duct directs a secondary exhaust stream emitted from the secondary combustor into the mixing duct. - View Dependent Claims (18, 19, 20)
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Specification