Patent US4900231A successfully refreshed from Google Patents.
US4900231A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Auxiliary compressor air supply for an aircraft
Assignee: Boeing Co
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Filing: 1986-05-30
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Granted: 1990-02-13
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Expires: 2006-05-30
Abstract
Abstract Engine (10) shaft power provides a first input (16) for a differential gear box (18). This input (16) is additive in a gear box (18) to a second input (30) from an electric motor (32). The output (22) of the gear box (18) powers a rotor (24) of an auxiliary compressor (12) which produces compressed air for providing needed pneumatic services aboard the aircraft. Compressor rotor speed is sensed (sensor 40) and used for controlling operating current (via controller 42 and frequency converter 44) to the electric motor (32). Motor (32) is an electronically commutated brushless electric motor having a high torque output which is substantially linearly proportional to the input current.
Inventors
- 👤 Norman J. Kennedy
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 14:29
CPC Classifications
B; B64; B64D; B64D41/00
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
126 words
An air supply system for an aircraft, comprising: a propulsion engine having an output shaft; an air compressor separate from said engine having an inlet, an outlet and a rotor; differential gearing means having an output connected to the compressor rotor, a first input drivenly connected to the output shaft of the aircraft engine, and a second input; an electric motor drivingly connected to the second input; and means responsive to a condition of the compressor for operating the electric motor in an amount sufficient to provide a predetermined desired amount of input drive to the differential gearing, for helping to drive the compressor rotor during periods of low output from the engine shaft, for the purpose of establishing a desired output from the air compressor.
Claim 2
Dependent Claim
126 words
An air supply system for an aircraft, comprising: a propulsion engine having an output shaft; an air compressor separate from said engine having an inlet, an outlet and a rotor; differential gearing means having an output connected to the compressor rotor, a first input drivenly connected to the output shaft of the aircraft engine, and a second input; an electric motor drivingly connected to the second input; and means responsive to a condition of the compressor for operating the electric motor in an amount sufficient to provide a predetermined desired amount of input drive to the differential gearing, for helping to drive the compressor rotor during periods of low output from the engine shaft, for the purpose of establishing a desired output from the air compressor.
Claim 3
Dependent Claim
38 words
An air supply system according to claim 1, wherein the first input to the differential gearing means comprises a shaft which includes a one-way drive coupling arranged to prevent the second input from back driving the first input.
Claim 4
Dependent Claim
32 words
An air supply system according to claim 1, wherein the second input comprises a shaft which includes a one-way drvie coupling for preventing the first input from back driving the second input.
Claim 5
Dependent Claim
17 words
An air supply system according to claim 1, wherein the electric motor is a variable speed motor.
Claim 6
Dependent Claim
55 words
An air supply system according to claim 4, where the means responsive to a condition of the compressor for operating the electric motor comprises control means responsive to the speed of rotation of the compressor rotor, to produce a signal, and means responsive to said signal for controlling the output speed of the electric motor.
Claim 7
Dependent Claim
33 words
An air supply system according to claim 1, wherein the eletric motor is of a type which produces an output torque that is substantially linearly proportional to the input current to the motor.
Claim 8
Dependent Claim
36 words
An air supply system according to claim 6, wherein the means responsive to a condition of the compressor for operating the electric motor comprises control means responsive to the speed of rotation of the compressor rotor.
Claim 9
Dependent Claim
18 words
An air supply system according to claim 6, wherein the electric motor is a brushless permanent magnet motor.
Claim 10
Independent Claim
99 words
A method of generating a supply of compressed air aboard an aircraft, for use to provide pneumatic services aboard the aircraft, comprising: providing an auxiliary compressor of a type including a rotor; providing a mechanical drive connection between the aircraft engine and the compressor rotor, so that the rotor is driven by engine shaft power; using the engine shaft power alone to drive the compressor rotor during cruise power and higher power operation of the engine; using an electric motor in conjunction with engine shaft power for driving the compressor rotor during low power operation of the aircraft engine.
Claim 11
Independent Claim
99 words
A method of generating a supply of compressed air aboard an aircraft, for use to provide pneumatic services aboard the aircraft, comprising: providing an auxiliary compressor of a type including a rotor; providing a mechanical drive connection between the aircraft engine and the compressor rotor, so that the rotor is driven by engine shaft power; using the engine shaft power alone to drive the compressor rotor during cruise power and higher power operation of the engine; using an electric motor in conjunction with engine shaft power for driving the compressor rotor during low power operation of the aircraft engine.
Claim 12
Dependent Claim
42 words
A method according to claim 9, comprising sensing a condition of the compressor to produce a signal indicative of the output of the compressor, and using said signal for controlling the electric motor, for establishing a desired output from the air compressor.
Claim 13
Dependent Claim
72 words
A method according to claim 9, comprising providing a differential gear box which includes a first input drivenly connected to engine shaft power, a second input drivenly connected to the electric motor, and an output connected to the compressor rotor, and using said differential gear box to add together the input from engine shaft power and the input from the electric motor, to provide a combined out for driving the compressor rotor.
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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) | 1993-02-12 | 1993-08-14 | 1994-02-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1997-02-12 | 1997-08-14 | 1998-02-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2001-02-12 | 2001-08-14 | 2002-02-13 | $7700.00 | Window Closed / Lapsed |