Compressor load control for an auxiliary power unit

• US 4,370,560 A
• Filed: 03/09/1981
• Issued: 01/25/1983
• Est. Priority Date: 10/15/1979
• Status: Expired due to Fees

• Current Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Markunas, Albert L., Glennon, Timothy F., Faulkner, Dennis T.
• Primary Examiner(s): Truhe, J. V.
• Assistant Examiner(s): Wade, Shelley
• Application Number:
  US06/242,058
• Time in Patent Office: 687 Days
• Field of Search: 290/40 A, 290/40 B, 290/40 C, 290/40 F, 290/40 R, 244/53 R, 244/53 B, 60/39.16 R, 60/39.25
• US Class Current: 290/40.00C
• CPC Class Codes: F02C 9/58 with control of a variable-pitch propeller
• CPC Class Codes: F04D 27/02 Surge control surge detection F04D27/001
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)

Abstract

An auxiliary power unit for an aircraft drives an electrical generator and an air compressor. The auxiliary power unit is primarily intended for operation with the aircraft on the ground when other aircraft power systems are shut down. The auxiliary power unit may, however, be used in an emergency to supplement the main aircraft generating system, with the aircraft airborne. When the auxiliary power unit generator is used in conjunction with the aircraft generating system, inlet air to the compressor is controlled to vary the compressor load on the power unit to minimize power unit speed changes and electrical frequency transients.

Claims

1. In an aircraft auxiliary power unit, having an engine, a generator driven by the engine, an air compressor driven by the engine, the speeds of the engine, air compressor and generator being directly related,

a fuel valve for the engine, and an engine control having means responsive to engine speed for controlling the fuel valve to maintain constant engine speed,

an improved transient engine speed control, comprising:

means for varying the loading of the air compressor on said engine; and

means responsive to the speed of one of the engine, generator or compressor for varying the compressor loading simultaneously with control of said fuel valve to minimize variation of the speed of the output frequency of the generator.

2. The auxiliary power unit control of claim 1 for a power unit in which the engine is a turbine driven by gas from a rotary gas generator and in which the transient control includes:

means responsive to aircraft altitude to establish a desired gas producer speed;

means for measuring the actual gas producer speed;

means for combining the desired gas producer speed and the actual gas producer speed to determine a gas producer speed error;

said engine speed responsive means including means for combining engine speed with maximum engine speed to determine engine speed error; and

means for adding said gas producer speed error and engine speed error to produce a composite error for varying compressor loading.

3. The auxiliary power unit of claim 1, in which the engine is a turbine and the transient control includes:

means to establish a desired turbine speed;

means for measuring the actual turbine speed;

means combining the desired and actual turbine speed to establish a turbine speed error signal, said turbine speed error signal operative to control the fuel valve and to affect the positioning of the inlet guide vanes.