Back to results
US 10,865,987 B2Granted
Sequential combustor and method for operating the same
AssigneeAnsaldo Energia Switzerland AG
InventorsKhawar Syed, Madhavan Narasimhan Poyyapakkam, Franklin Marie Genin
Life of this patent
Estimating the term…
Abstract
The present invention generally relates to a sequential combustor for a gas turbine having second and/or subsequent stages of a re-heat, sequential or axially-staged combustion system. A variation in Mach number along the flow path can be used to control static temperature variation, which in turn influences the progress of auto-ignition reactions that eventually lead to the onset of combustion.
Claims12
A sequential annular combustor for a gas turbine, comprising:
- a premixing section having a first diameter, a radially converging duct, and a radially diverging duct in serial flow arrangement;
- a combustion chamber having a second diameter greater than the first diameter arranged downstream of the premixing section, the combustion chamber including a diffuser at an upstream end of the combustion chamber;
- and
- a plurality of radially extending vanes extending from a point in the radially converging duct of the premixing section to a point in the diffuser of the combustion chamber;
- and
- one or more passages formed between adjacent vanes of the plurality of vanes, each passage having a contour including a circumferentially convergent section and a circumferentially divergent section,
- wherein the circumferentially divergent section of each passage extends downstream from the circumferentially convergent section of each passage and the diffuser having an expansion angle for producing rapid flow deceleration of oxidant and fuel.
4 more elements
A sequential annular combustor for a gas turbine, comprising:
- a premixing section having a radially converging duct and a radially diverging duct in serial flow arrangement;
- a combustion chamber arranged downstream of the premixing section, the combustion chamber including a diffuser at an upstream end of the combustion chamber;
- a plurality of radially extending vanes extending from a point in the radially converging duct of the premixing section to a point in the diffuser of the combustion chamber;
- and
- one or more passages formed between adjacent vanes of the plurality of vanes, each passage having a contour including a circumferentially convergent section and a circumferentially divergent section,
- wherein the circumferentially divergent section of each passage extends downstream from the circumferentially convergent section of each passage and the diffuser having an expansion angle for producing rapid flow deceleration of oxidant and fuel.
3 more elements
Method for operating a sequential annular combustor for a gas turbine, the sequential annular combustor having:
- a premixing section having a first diameter a radially converging duct and a radially diverging duct in serial flow arrangement;
- a combustion chamber having a second diameter greater than the first diameter arranged downstream of the premixing section, the combustion chamber including a diffuser at an upstream end of the combustion chamber;
- and
- a plurality of radially extending vanes extending from a point in the radially converging duct of the premixing section to a point in the diffuser of the combustion chamber;
- and
- one or more passages formed between adjacent vanes of the plurality of vanes, each passage having a contour including a circumferentially convergent section and a circumferentially divergent section,
- wherein the circumferentially divergent section of each passage extends downstream from the circumferentially convergent section of each passage and the diffuser having an expansion angle for producing rapid flow deceleration of oxidant and fuel;
- said premixing section being configured to receive and premix a flow of oxidant and fuel wherein the method comprises:
- admitting the flow of oxidant and fuel within one or more of said convergent sections for acceleration to a velocity correspondent to a Mach number substantially equal to 0.5 or greater.
6 more elements
Dependencies are inferred from the claim text.