GAS TURBINE ENGINE TURBINE BLADE TIP ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD

摘要

A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.

主权项

1. A method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine that is installed on an aircraft and that includes a turbine shroud and a turbine case, the method comprising the steps of:
processing aircraft data to determine when the aircraft is flying at altitude cruise conditions; directing compressor discharge air to impinge upon at least a portion of the turbine shroud when the aircraft is not flying at altitude cruise conditions; and upon determining that the aircraft is flying at altitude cruise conditions, directing the compressor discharge air to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.