System and methods for controlling surge margin in the compressor section of a gas turbine engine
AssigneeRolls-Royce North American Technologies Inc.
InventorsBenjamin Michael Iwrey, Graham Adam Burkholder
Life of this patent
Estimating the term…
Abstract
Systems and methods are disclosed for controlling surge margin in the compressor section of a gas turbine engine. A first compressor section and a second compressor section are in fluid communication with a bypass conduit. An auxiliary turbine and discharge conduit are positioned in the bypass conduit. Fluid flow from the compressor sections into the bypass conduit is controlled by bypass control valves.
Claims20
A system for controlling surge margin in a compressor section of a gas turbine engine, the system comprising:
- a first compressor section comprising:
- one or more compressor stages defining a first compressor section flowpath;
- and
- a first compressor section discharge in fluid communication with the first compressor section flowpath;
- a first compressor section bypass port positioned along the first compressor section and in fluid communication with the first compressor flowpath;
- a second compressor section comprising:
- one or more compressor stages defining a second compressor section flowpath, the second compressor section flowpath in fluid communication with the first compressor section flowpath;
- and
- a second compressor section discharge in fluid communication with the second compressor section flowpath;
- a second compressor section bypass port positioned along the second compressor section and in fluid communication with the second compressor section flowpath;
- a bypass conduit, extending between the first compressor section bypass port and the second compressor section bypass port;
- a first compressor section bypass control valve positioned in the bypass conduit downstream of the first compressor section bypass port;
- a second compressor section bypass control valve positioned in the bypass conduit downstream of the second compressor section bypass port;
- an auxiliary turbine positioned in the bypass conduit between the first compressor section bypass control valve and the second compressor section bypass control valve;
- a discharge conduit coupled to and in fluid communication with the bypass conduit between the auxiliary turbine and the second compressor section bypass control valve;
- and
- a discharge control valve positioned in the discharge conduit.
A system for controlling surge margin in a compressor section of a gas turbine engine, the system comprising:
- a first compressor section;
- a first compressor section bypass port positioned along the first compressor section and in fluid communication with the first compressor section;
- a second compressor section in fluid communication with and downstream of the first compressor section;
- a bypass conduit in fluid communication with the first compressor section bypass port and the second compressor section;
- a first compressor section bypass control valve coupled with the bypass conduit downstream of the first compressor section bypass port;
- a second compressor section bypass control valve coupled with the bypass conduit downstream of the second compressor section;
- an auxiliary turbine in fluid communication with the bypass conduit between the first compressor section bypass control valve and the second compressor section bypass control valve;
- a discharge conduit coupled with and in fluid communication with the bypass conduit downstream of the auxiliary turbine and the second compressor section bypass control valve;
- and
- a discharge control valve coupled with the discharge conduit.
Dependencies are inferred from the claim text.