Gas turbine engine with progressive stall recovery
AssigneeUnited Technologies Corporation
InventorsMatthew D. Teicholz, Stewart B. Hatch, Wyatt S. Daentl
Life of this patent
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Abstract
A control system for a gas turbine engine includes a processing system operable to control a speed of the gas turbine engine and a memory system. The memory system is operable to store instructions executable by the processing system to determine at least one performance parameter associated with a stall condition of the gas turbine engine and to incrementally adjust an acceleration rate of the gas turbine engine based on detecting a degraded stall line limit according to the at least one performance parameter.
Claims20
A control system for a gas turbine engine, the control system comprising:
- a processing system operable to control a speed of the gas turbine engine;
- and
- a memory system operable to store instructions executable by the processing system to determine at least one performance parameter associated with a stall condition of the gas turbine engine and to incrementally reduce an acceleration rate of the gas turbine engine based on detecting a degraded stall line limit of the gas turbine engine prior to reaching a stall line indicative of normal operation of the gas turbine engine according to the at least one performance parameter.
A gas turbine engine of an aircraft, the gas turbine engine comprising:
- a compressor section;
- a turbine section;
- and
- a control system comprising:
- a processing system operable to control a speed of a spool that interconnects the compressor section and the turbine section;
- and
- a memory system operable to store instructions executable by the processing system to determine at least one performance parameter associated with a stall condition of the gas turbine engine and to incrementally reduce an acceleration rate of the gas turbine engine based on detecting a degraded stall line limit of the gas turbine engine prior to reaching a stall line indicative of normal operation of the gas turbine engine according to the at least one performance parameter.
A method for progressive stall recovery of a gas turbine engine, the method comprising:
- determining, by a control system, at least one performance parameter associated with a stall condition of the gas turbine engine;
- and
- incrementally reducing an acceleration rate of the gas turbine engine based on detecting a degraded stall line limit of the gas turbine engine prior to reaching a stall line indicative of normal operation of the gas turbine engine according to the at least one performance parameter.
Dependencies are inferred from the claim text.