Patent US4462561A successfully refreshed from Google Patents.
US4462561A
Expired / Lapsed
US
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Energy efficient ECS powered by a variable voltage/variable frequency power system
Assignee: Lockheed Martin Corp
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Filing: 1982-05-27
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Granted: 1984-07-31
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Expires: 2002-05-27
Abstract
Abstract The invention is an ECS system designed to utilize an induction motor (12) and a cabin compressor (14) for providing pressurized air that serves as a source of energy for heating, cooling, pressurizing and other air needs of modern aircraft. An aircraft engine driven generator, preferably a permanent-magnet generator (of the samarium-cobalt, SmCo, type), furnishes variable-voltage/variable frequency, VV/VF, power to the motor (12). The electric motor itself in the preferred embodiment is a highly reliable squirrel-cage induction motor (12) powered directly from the VV/VF supply, with the result that its speed is proportional to the generator frequency, which in turn is dependent on the aircraft engine speed. The main cabin compressor (14) and a secondary (auxiliary) supercharging compressor (18) are both mounted on the motor shaft. The motor-compressor configuration is further characterized in that the ac motor has pole-changing winding (typically two), which permits two speed operation, while the cabin compressor is provided with inlet guide vanes (16). The interactive combination of these two features makes it possible to furnish the requisite air mass flow and pressurization levels over the conditions of variable air density and variable atmospheric pressure, as the airplane operates throughout its flight envelope.
Inventors
- 👤 Michael J. Cronin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 21:54
CPC Classifications
B; B64; B64D; B64D13/00; B64D13/06; F; F04; F04D; F04D27/00; F04D27/02; F04D27/0261; B64D2013/0603; B64D2013/0644; F25; F25B; F25B9/00; F25B9/002; F25B9/004; Y; Y02; Y02B; Y02B30/00; Y02B30/70; Y02T; Y02T50/00; Y02T50/50; Y10; Y10S; Y10S62/00; Y10S62/05
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
325 words
In an aircraft having at least one engine, an auxiliary power unit and an environmental control system having a boot-strap cooling system including a main cabin compressor driven by an induction motor, said motor capable of running in a two- or four-pole configuration, the method of controlling the output of said compressor comprising the steps of: providing an external electrical power at a first-frequency and first-voltage level to said induction motor in said two-pole configuration causing said compressor to run at a first RPM when said engine and said auxiliary power unit are off; providing electrical power from said auxiliary power unit at a second frequency and second voltage both double said first frequency and voltage to said induction motor in said four-pole configuration causing said main cabin compressor to run at said first RPM; providing electrical power at said first frequency and said first voltage level from said engine running at approximately 50% operating RPM to said induction motor in said two-pole configuration causing said main cabin compressor to run at said first RPM; providing electrical power from said engine running at maximum operating RPM at taking off and climbing at said second frequency and said second voltage level to said induction motor in said four-pole configuration causing said compressor to run at said first RPM; providing electrical power from said engine running at maximum operating RPM at altitude and cruise at said second frequency and said second voltage level to said induction motor in said two-pole configuration causing said main cabin compressor to run at a second RPM twice said first RPM; and providing a supercharging compressor in series with said main cabin compressor when said engine RPM is reduced between 10 and 20 percent and said second frequency and second voltage level is reduced proportionately, said supercharging compressor making up any loss of output from said main cabin compressor due to a reduction in RPM when said aircraft is descending from altitude.
Claim 2
Dependent Claim
325 words
In an aircraft having at least one engine, an auxiliary power unit and an environmental control system having a boot-strap cooling system including a main cabin compressor driven by an induction motor, said motor capable of running in a two- or four-pole configuration, the method of controlling the output of said compressor comprising the steps of: providing an external electrical power at a first-frequency and first-voltage level to said induction motor in said two-pole configuration causing said compressor to run at a first RPM when said engine and said auxiliary power unit are off; providing electrical power from said auxiliary power unit at a second frequency and second voltage both double said first frequency and voltage to said induction motor in said four-pole configuration causing said main cabin compressor to run at said first RPM; providing electrical power at said first frequency and said first voltage level from said engine running at approximately 50% operating RPM to said induction motor in said two-pole configuration causing said main cabin compressor to run at said first RPM; providing electrical power from said engine running at maximum operating RPM at taking off and climbing at said second frequency and said second voltage level to said induction motor in said four-pole configuration causing said compressor to run at said first RPM; providing electrical power from said engine running at maximum operating RPM at altitude and cruise at said second frequency and said second voltage level to said induction motor in said two-pole configuration causing said main cabin compressor to run at a second RPM twice said first RPM; and providing a supercharging compressor in series with said main cabin compressor when said engine RPM is reduced between 10 and 20 percent and said second frequency and second voltage level is reduced proportionately, said supercharging compressor making up any loss of output from said main cabin compressor due to a reduction in RPM when said aircraft is descending from altitude.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-07-31 | 1988-01-30 | 1988-07-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-07-31 | 1992-01-30 | 1992-07-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-07-31 | 1996-01-30 | 1996-07-31 | $7700.00 | Window Closed / Lapsed |