Aircraft environmental control system inlet flow control

• US 9,205,927 B2
• Filed: 04/10/2013
• Issued: 12/08/2015
• Est. Priority Date: 04/10/2013
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Shepard, Eric, Wolownik, Todd
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): AMAR, MARC J
• Application Number:
  US13/859,978
• Publication Number:
  US 20140305130A1
• Time in Patent Office: 972 Days
• US Class Current: 1/1
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 2013/0611 combined with auxiliary power units (APU's)
• CPC Class Codes: B64D 2013/0618 with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
• CPC Class Codes: B64D 2013/0648 with energy recovery means, e.g. using turbines
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/141 of working fluid
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F05D 2270/313 Air temperature
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

A system and method for controlling bleed air flow into an air cycle machine that includes a bleed air inlet and a conditioned air outlet is provided. The system and method include discharging bleed air from an operating gas turbine engine, sensing exhaust gas temperature (EGT) of the gas turbine engine, sensing conditioned air temperature at the conditioned air outlet, and controlling bleed air flow into the air cycle machine based on the sensed EGT and on the sensed conditioned air temperature.

Claims

1. An aircraft environmental control system, comprising:

an air cycle machine having a bleed air inlet and a conditioned air outlet, the air cycle machine adapted to selectively receive a flow of bleed air at the bleed air inlet and configured, upon receipt thereof, to discharge conditioned air from the conditioned air outlet, the conditioned air having a temperature lower than the bleed air;

an inlet flow control valve coupled to the bleed air inlet and adapted to receive bleed air discharged from a gas turbine engine, the inlet flow control valve coupled to receive valve commands and configured, in response to the valve commands, to move between a closed position and a plurality of open positions;

an exhaust gas temperature (EGT) sensor configured to sense EGT of the gas turbine engine and supply an EGT signal representative thereof;

a conditioned air temperature sensor configured to sense the temperature of the conditioned air and supply a conditioned air temperature signal representative thereof; and

a controller coupled to receive the EGT signal and the conditioned air temperature signal and, based on the EGT and conditioned air temperature signals, configured to supply valve commands to the inlet flow control valve to thereby control the flow of bleed air into the bleed air inlet.

2. The system of claim 1, wherein the air cycle machine comprises:

a compressor coupled to receive the flow of bleed air supplied to the bleed air inlet, the compressor configured to compress the bleed air and discharge the compressed bleed air; and

a turbine coupled to receive the compressed bleed air and supply the conditioned air to the conditioned air outlet.

3. The system of claim 2, wherein the air cycle machine further comprises:

a primary heat exchanger coupled to receive the flow of bleed air supplied to the bleed air inlet and a flow of cooling air from a cooling air source, the primary heat exchanger configured to transfer heat from the bleed air to the cooling air and supplied cooled bleed air to the compressor.

4. The system of claim 3, wherein the air cycle machine further comprises:

a secondary heat exchanger coupled to receive the compressed bleed air discharged from the compressor and the flow of cooling air from the cooling air source, the secondary heat exchanger configured to transfer heat from the compressed bleed air to the cooling air and supply cooled compressed air to the turbine.

5. The system of claim 1, wherein the controller is further configured, in response to the EGT signal and the conditioned air temperature signal, to supply gas turbine engine speed commands representative of commanded rotational speeds.

6. The system of claim 5, further comprising:

a gas turbine engine configured to rotate at a rotational speed and supply the flow of bleed air to the air cycle machine; and

an engine control unit in operable communication with the gas turbine engine and coupled to receive the gas turbine engine speed commands from the controller, the engine control unit configured, in response to the gas turbine engine speed commands, to control the gas turbine engine to rotate at the commanded rotational speed.

7. The system of claim 1, wherein the gas turbine engine is configured as an auxiliary power unit (APU).

8. An aircraft environmental control system, comprising:

an auxiliary power unit (APU) having a bleed air outlet, the APU configured to selectively discharge bleed air from the bleed air outlet;

an air cycle machine having a bleed air inlet and a conditioned air outlet, the bleed air inlet coupled to selectively receive the bleed air discharged from the APU, the air cycle machine configured, upon receipt of the bleed air, to discharge conditioned air from the conditioned air outlet, the conditioned air having a temperature lower than the bleed air;

an inlet flow control valve coupled between the bleed air outlet and the bleed air inlet to receive the bleed air discharged from the APU, the inlet flow control valve coupled to receive valve commands and configured, in response to the valve commands, to move between a closed position and a plurality of open positions;

an exhaust gas temperature (EGT) sensor configured to sense EGT of the APU and supply an EGT signal representative thereof;

a conditioned air temperature sensor configured to sense the temperature of the conditioned air and supply a conditioned air temperature signal representative thereof; and

a controller coupled to receive the EGT signal and the conditioned air temperature signal and, based on the EGT and conditioned air temperature signals, configured to supply valve commands to the inlet flow control valve to thereby control the flow of bleed air into the bleed air inlet.

9. The system of claim 8, wherein the air cycle machine comprises:

a compressor coupled to receive the flow of bleed air supplied to the bleed air inlet, the compressor configured to compress the bleed air and discharge the compressed bleed air; and

a turbine coupled to receive the compressed bleed air and supply the conditioned air to the conditioned air outlet.

10. The system of claim 9, wherein the air cycle machine further comprises:

a primary heat exchanger coupled to receive the flow of bleed air supplied to the bleed air inlet and a flow of cooling air from a cooling air source, the primary heat exchanger configured to transfer heat from the bleed air to the cooling air and supplied cooled bleed air to the compressor.

11. The system of claim 10, wherein the air cycle machine further comprises:

a secondary heat exchanger coupled to receive the compressed bleed air discharged from the compressor and the flow of cooling air from the cooling air source, the secondary heat exchanger configured to transfer heat from the compressed bleed air to the cooling air and supply cooled compressed air to the turbine.

12. The system of claim 8, wherein the controller is further configured, in response to the EGT signal and the conditioned air temperature signal, to supply APU speed commands representative of commanded rotational speeds.

13. The system of claim 12, further comprising:

an engine control unit in operable communication with the APU and coupled to receive the APU speed commands from the controller, the engine control unit configured, in response to the APU speed commands, to control the APU to rotate at the commanded rotational speed.