초록 ▼

A system and method are provided for effectively removing ice that may have formed on gas turbine engine compressor inlet guide vanes and/or preventing, or at least inhibiting, reformation of ice on gas turbine engine compressor inlet guide vanes after the ice has been removed. A determination is ma

A system and method are provided for effectively removing ice that may have formed on gas turbine engine compressor inlet guide vanes and/or preventing, or at least inhibiting, reformation of ice on gas turbine engine compressor inlet guide vanes after the ice has been removed. A determination is made as to whether actual inlet guide vane position differs from the commanded inlet guide vane position by a predetermined amount. If so, then the inlet guide vanes are repeatedly commanded to move in at least two predetermined directions to remove ice that may have formed on the inlet guide vanes.

대표청구항 ▼

What is claimed is: 1. A method of removing ice formed on the inlet guide vanes of a compressor, comprising the steps of: determining if compressor inlet temperature is below a first predetermined temperature value; determining if actual inlet guide vane position differs from commanded inlet guide

What is claimed is: 1. A method of removing ice formed on the inlet guide vanes of a compressor, comprising the steps of: determining if compressor inlet temperature is below a first predetermined temperature value; determining if actual inlet guide vane position differs from commanded inlet guide vane position by a predetermined error magnitude; and repeatedly commanding the inlet guide vanes to move in at least two predetermined directions if (i) the actual inlet guide vane position differs from commanded inlet guide vane position by the predetermined error magnitude and (ii) the compressor inlet temperature is below the predetermined temperature value. 2. The method of claim 1, wherein the compressor is installed in an aircraft, and wherein the method further comprises: determining if the aircraft is in a predetermined state; and repeatedly commanding the inlet guide vanes to move in the at least two predetermined directions if (i) the actual inlet guide vane position differs from commanded inlet guide vane position by the predetermined error magnitude, (ii) the compressor inlet temperature is below the predetermined temperature value, and (iii) the aircraft is in the predetermined state. 3. The method of claim 2, wherein the compressor forms part of an auxiliary power unit (APU), and wherein the predetermined state comprises: the compressor is not supplying main engine start air; the aircraft is not in flight; and the APU is in a predetermined state. 4. The method of claim 1, wherein the step of repeatedly commanding the inlet guide vanes to move in at least two predetermined directions comprises: commanding the inlet guide vanes to move between a first position and a second position at a predetermined period. 5. The method of claim 4, wherein the predetermined period is 60 seconds. 6. The method of claim 4, wherein: the inlet guide vanes are repeatedly commanded to move, at the predetermined period, to the first position for a first predetermined time period and to the second position for a second predetermined time period. 7. The method of claim 6, wherein: the first predetermined time is about 3 seconds; and the second predetermined time is about 1 second. 8. The method of claim 1, further comprising: if actual inlet guide vane position does not differ from commanded inlet guide vane position by the predetermined error magnitude, repeatedly moving the inlet guide vanes from an initial position to a more open position and then back to the initial position. 9. The method of claim 8, wherein the compressor is installed in an aircraft and is configured to supply bleed air, and wherein the method further comprises: determining if the aircraft is in a predetermined state; determining if the compressor is supplying bleed air; and repeatedly moving the inlet guide vanes from an initial position to a more open position and then back to the initial position (i) the actual inlet guide vane position does not differ from commanded inlet guide vane position by the predetermined error magnitude, (ii) the aircraft is in the predetermined state, and (iii) the compressor is not supplying bleed air. 10. A method of removing ice formed on the inlet guide vanes of a compressor, comprising the steps of: determining if actual inlet guide vane position differs from commanded inlet guide vane position by a predetermined error magnitude; if actual inlet guide vane position differs from commanded inlet guide vane position by the predetermined error magnitude, repeatedly commanding the inlet guide vanes to move in at least two predetermined directions; and if actual inlet guide vane position does not differ from commanded inlet guide vane position by the predetermined error magnitude, repeatedly moving the inlet guide vanes from an initial position to a more open position and then back to the initial position. 11. A method of removing ice formed on the inlet guide vanes of a compressor, comprising the steps of: determining if actual inlet guide vane position differs from commanded inlet guide vane position by a predetermined error magnitude; if actual inlet guide vane position differs from commanded inlet guide vane position by the predetermined error magnitude, repeatedly commanding the inlet guide vanes to move, at a predetermined period, to a first position for a first predetermined time period and to a second position for a second predetermined time period. 12. The method of claim 11, wherein the predetermined period is 60 seconds. 13. The method of claim 11, wherein: the first predetermined time is about 3 seconds; and the second predetermined time is about 1 second.