Aircraft engine starter integrated boundary bleed system

• US 5,136,837 A
• Filed: 03/06/1990
• Issued: 08/11/1992
• Est. Priority Date: 03/06/1990
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Davison, Samuel H.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US07/489,150
• Time in Patent Office: 889 Days
• Field of Search: 60/39.07, 60/39.183, 60/39.141, 60/39.45, 60/39.83, 98/1.5, 244/118.5, 244/209, 244/58
• US Class Current: 60/785
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F04D 25/02 Units comprising pumps and their driving means
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An aircraft gas turbine engine is provided with a compressed air supply system generally used for meeting customer or aircraft bleed air requirements. The compressed air supply system comprises an auxiliary compressor, a means for mechanically driving the system from a rotor of the gas turbine rotor, and a cycle varying means, such as a variable speed drive, for operating the auxiliary compressor cycle independently of the aircraft gas turbine engine compressor cycle. The preferred embodiment provides a means for bleeding boundary layer air off the nacelle or another part of the aircraft outer skin and using it as a source of air for the auxiliary compressor. One embodiment includes an air turbine on a common shaft with the auxiliary compressor and a means to direct an unused portion of the airflow form the auxiliary compressor to the air turbine to help power the auxiliary compressor and another embodiment includes a means to direct compressed startling air to the air turbine for on ground and in flight starting of the gas turbine engine through the variable speed drive and a mechanical linkage to the high rotor of the gas turbine engine.

Claims

1. An apparatus for supplying an aircraft with auxiliary compressed air and integral with an aircraft propulsive gas turbine engine having a rotor, said apparatus comprising:

an auxiliary compressor for supplying the auxiliary compressed air,

a means for mechanically driving said auxiliary compressor from the rotor of the gas turbine engine,

a cycle varying means for operating the cycle of said auxiliary compressor independently from the cycle of the aircraft gas turbine engine,

an air turbine on a common shaft with said auxiliary compressor,

a means capable of supplying a portion of the auxiliary compressed air from said auxiliary compressor to said air turbine, and

a means for supplying compressed starting air to said air turbine.

2. An apparatus as claimed in claim 1 wherein said cycle varing means comprises a variable speed drive in mechanical drive relationship with said auxiliary compressor and drivingly connected to the gas turbine engine rotor.

3. An apparatus as claimed in claim 2 wherein said cycle varying means further comprises an electronic control system for controlling said apparatus.

4. An apparatus as claimed in claim 3 wherein the compressed starting air is supplied from the engine crossbleed system.

5. An apparatus for bleeding boundary layer air and supplying aircraft auxiliary compressed air and integral with an aircraft propulsive gas turbine engine comprising:

a bleed means for collecting boundary layer air from an aircraft'"'"'s outer skin,

an auxiliary compressor, for supplying the auxiliary compressed air, in fluid supply communication with said bleed means effective for compressing bleed air supplied from said bleed means,

a first ducting means to convey at least a portion of the compressed air from said auxiliary compressor to supply aircraft bleed air requirements,

a transmission means connecting said compressor to the rotor of the gas turbine engine in a manner effective for driving said compressor off a rotor of the engine,

an air turbine drivingly connected to said compressor, and

a starting air supply means in switchable fluid supply communication with and effective for supplying compressed starting air to said air turbine.

6. An apparatus as claimed in claim 5 further comprising an alternative air supply in selectable fluid supply communication with said auxiliary compressor and a selecting valve disposed between said bleed means and said alternate air supply, said selecting valve in fluid supply communication with said auxiliary compressor and effective for controlling air flow to auxiliary compressor from said bleed means and said alternate air supply.

7. An apparatus as claimed in claim 6 wherein said transmission means includes a variable speed drive located in driving relationship between the engine rotor and said compressor.

8. An apparatus as claimed in claim 6 further comprising:

a second ducting means for flowing a second portion of the compressed air from said compressor to said air turbine for powering said air turbine.

9. An apparatus as claimed in claim 7 further comprising:

a second ducting means for flowing a second portion of the compressed air from said compressor to said air turbine for powering said air turbine.

10. An apparatus as claimed in claim 9 further comprising:

a starting air supply means effective for supplying starting air to said air turbine.

11. An apparatus as claimed in claim 10 further comprising:

an electronic control system for controlling said variable speed drive.

12. An apparatus as claimed in claim 11 wherein said electronic control system is effective for selectively controlling said first and second ducting means and said starting air supply means.

13. An apparatus as claimed in claim 12 further comprising:

a first valve means for selecting either starting air or auxiliary compressor discharge air to be supplied to said air turbine.

14. An apparatus as claimed in claim 13 wherein said starting air supply system includes a means for selectively using ground starting air or in flight starting air for supplying starting air to said air turbine.

15. An apparatus as claimed in claim 14 wherein said second valve means is controlled by said electronic control.

16. An apparatus as claimed in claim 12 further comprising:

a first valve means for selecting either starting air or auxiliary compressor discharge air to be supplied to said air turbine.

17. An apparatus as claimed in claim 8 further comprising:

a dump means for selectively flowing a third portion of the compressed air from said auxiliary compressor to a dump, said dump means including a dump valve for controlling said third portion of compressed air to be flowed.

18. An apparatus as claimed in claim 17 further comprising an air turbine exhaust means including a turbine exhaust duct for ducting at least a portion of the outflow of said air turbine to said dump means downstream of said dump valve.

19. An apparatus as claimed in claim 18 wherein said dump means is a cooling means and said dump is an area of the engine that requires cooling.

20. An apparatus as claimed in claim 19 wherein said area of the engine that requires cooling is located within the core cowling.

21. An apparatus as claimed in claim 19 wherein said area of the engine that requires cooling is an area containing engine accessories.