Gas turbine engine/load compressor power plants

• US 4,627,234 A
• Filed: 06/15/1983
• Issued: 12/09/1986
• Est. Priority Date: 06/15/1983
• Status: Expired due to Term

• Current Assignee: Sundstrand Corporation 4751 Harrison Rockford IL
• Original Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Schuh, Paul A.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US06/504,441
• Time in Patent Office: 1,273 Days
• Field of Search: 60/39.141, 60/39.281, 60/39.142, 417/805
• US Class Current: 60/39.281
• CPC Class Codes: F02C 3/085 the turbine being of the radial-flow type (radial-radial) F02C3/05 takes precedence
• CPC Class Codes: F02C 6/06 providing compressed gas F02C6/10 takes precedence
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F04D 27/0207 by bleeding, bypassing or recycling fluids influencing the boundary layer by an uncontrolled bleeding of the working fluid F04D29/681
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)
• CPC Class Codes: F05D 2270/091 in particular sudden load loss

Abstract

Single shaft, air breathing auxiliary power units having a single stage centrifugal load compressor driven by a gas turbine engine. The latter has a single stage centrifugal compressor and a single stage radial inflow turbine mounted in back-to-back relationship on the same shaft as the load compressor. Control systems for these auxiliary power units feature turbine exhaust gas temperature and turbine speed responsive fuel flow control; a bypass valve control which causes air to be dumped overboard when the pneumatic load demand drops to prevent load compressor surge; and an inlet guide vane control.

Claims

1. A single shaft gas turbine engine power plant comprising:

a power head and a radial load compressor driven by said power head, said power head being an air breathing gas turbine engine comprising a radial compressor;

a combustor for heating, and thereby adding energy to, the air discharged from said radial compressor; and

a radial gas turbine driven by hot gases flowing thereto from said combustor, said radial gas turbine being drive connected to the engine and load compressor; and

said power plant further comprising means for so scheduling a flow of fuel to said turbine engine combustor as to be simultaneously responsive to a radial gas turbine exhaust temperature and to gas turbine engine speed to thereby maintain the turbine exhaust temperature below selected maximums during start-up and acceleration of said gas turbine engine to a specified speed and to thereafter keep the gas turbine engine speed from exceeding a selected maximum;

said fuel flow scheduling means including means which is effective when the engine reaches a selected speed to switch the functioning of the scheduling means from a turbine exhaust gas temperature input mode of operation to an engine speed input mode of operation and a modulating type fuel flow control valve controllingly coupled to the means for switching the functioning of the fuel flow scheduling means;

said means for switching the functioning of the fuel flow scheduling means including a first gating means for transmitting a first, exhaust gas temperature responsive signal to an actuator of said fuel flow control valve, a second gating means for transmitting a second, turbine speed responsive signal to said actuator, and means operable when the engine reaches said selected speed to inactivate the first and activate the second of said gating means; and

said means for so scheduling the flow of fuel to said turbine engine combustor as to maintain the turbine exhaust gas temperature below said selected maximums comprising means for summing and providing a flow correction signal from a first signal indicative of measured turbine exhaust gas temperature and a second signal indicative of an exhaust gas set point temperature and means for establishing corrected minimum and maximum limits of the flow correction signal for the actuator of said fuel flow control valve.

2. A gas turbine engine power plant as defined in claim 1 which includes means for providing to said summing means a second signal as aforesaid which is a function of gas turbine engine speed.

3. A gas turbine engine power plant as defined in claim 1 which includes a modulating type fuel flow control valve and wherein the means for so scheduling the flow of fuel to said combustor as to maintain the speed of the power head turbine below the selected maximum comprises means for summing and providing a flow correction signal from a first signal indicative of measured turbine speed and a second signal indicative of setpoint turbine speed and means for converting the flow correction signal to a control signal for the actuator of said fuel flow control valve.

4. A gas turbine engine power plant as defined in claim 1 wherein the fuel flow scheduling means comprises a speed responsive means operable during the start-up acceleration of said gas turbine engine to said rated speed for limiting the flow of fuel to said combustor and thereby limiting a runaway in the event of a failure which renders said fuel flow scheduling means incapable of operating as aforesaid in response to measured turbine exhaust gas temperature.

5. A gas turbine engine power plant as defined in claim 4 wherein the fuel flow scheduling means comprises means for adjusting the maximum flow of fuel as limited by said speed responsive means to compensate for changes in the ambient temperature and pressure at the power head compressor inlet.

6. A gas turbine engine power plant as defined in claim 1 wherein the fuel flow scheduling means includes means for limiting the minimum and maximum flows of fuel to said combustor as functions of the ambient temperature and pressure at the power head compressor inlet.