US3842720A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Jet pump for aircraft cabin pressurization system
Assignee: PIPER AIRCRAFT CORP
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Filing: 1973-03-29
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Granted: 1974-10-22
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Expires: 1993-03-29
Abstract
Abstract The jet pump includes a primary nozzle in communication with the compressor section of the aircraft''s turbine engine whereby primary air is bled from the engine for delivery through the primary nozzle. A secondary nozzle surrounds the primary nozzle and lies in communication with ambient air. Primary and secondary air issuing through the primary and secondary nozzles flows into a mixing tube and then through a divergent section for delivery to the aircraft cabin. The jet pump functions, and without the aid of ancillary control devices, to provide an acceptable predetermined air flow rate for pressurizing the aircraft cabin throughout the full altitude range of the aircraft.
Inventors
- 👤 L Herr
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 06:04
CPC Classifications
B; B64; B64D; B64D13/00; B64D13/02
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
145 words
A pressurization system for an aircraft comprising the combination of an engine including a source of air under pressure, a jet pump for pressurizing the cabin in the aircraft, said jet pump including a primary nozzle in communication with the air under pressure from the engine, a secondary nozzle in communication with ambient air, a tube in communication with said nozzles on the downstream side thereof for receiving and mixing the air issuing from said nozzles, a divergent section at the opposite end of said mixing tube for receiving the mixed air from said nozzles and communicating it to the aircraft cabin, said mixing tube having a length to width ratio within a range of about 8 to 14, said jet pump being effective per se to provide an acceptable air flow rate for pressurizing the cabin throughout the full altitude range of the aircraft.
Claim 2
Dependent Claim
145 words
A pressurization system for an aircraft comprising the combination of an engine including a source of air under pressure, a jet pump for pressurizing the cabin in the aircraft, said jet pump including a primary nozzle in communication with the air under pressure from the engine, a secondary nozzle in communication with ambient air, a tube in communication with said nozzles on the downstream side thereof for receiving and mixing the air issuing from said nozzles, a divergent section at the opposite end of said mixing tube for receiving the mixed air from said nozzles and communicating it to the aircraft cabin, said mixing tube having a length to width ratio within a range of about 8 to 14, said jet pump being effective per se to provide an acceptable air flow rate for pressurizing the cabin throughout the full altitude range of the aircraft.
Claim 3
Dependent Claim
39 words
Apparatus according to claim 1 wherein the ratio of the cross-sectional area of said second nozzle at its throat to the cross-sectional area of said first nozzle at its throat is within a range of about 2 to 4.
Claim 4
Dependent Claim
36 words
Apparatus according to claim 1 wherein the ratio of the cross-sectional area of the mixing tube to the cross-sectional area of said first nozzle at its throat is within a range of about 2 to 4.
Claim 5
Dependent Claim
61 words
Apparatus according to claim 1 wherein, the ratio of the cross-sectional areas of said first and second nozzles at their throats being within a range of about 2 to 4, the ratio of the cross-sectional area of the mixing tube to the cross-sectional areas of said first and second nozzles at their throats lying within the ranges of 2 to 4.
Claim 6
Dependent Claim
18 words
Apparatus according to claim 1 wherein said mixing tube has a length to width ratio of about 11.4.
Claim 7
Dependent Claim
33 words
Apparatus according to claim 1 wherein the ratio of the cross-sectional area of said first nozzle at its throat to the cross-sectional area of said second nozzle at its throat is about 3.04.
Claim 8
Dependent Claim
30 words
Apparatus according to claim 1 wherein the ratio of the cross-sectional area of the mixing tube to the cross-sectional area of said first nozzle at its throat is about 3.04.
Claim 9
Dependent Claim
30 words
Apparatus according to claim 1 wherein the ratio of the cross-sectional area of the mixing tube to the cross-sectional area of said second nozzle at its throat is about 1.00.
Claim 10
Dependent Claim
31 words
Apparatus according to claim 1 wherein the ratio of the area of the outlet of said first nozzle to the area of the first nozzle at its throat is about 1.20.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-10-21 | 1978-04-22 | 1978-10-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-10-21 | 1982-04-22 | 1982-10-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-10-21 | 1986-04-22 | 1986-10-22 | $7700.00 | Window Closed / Lapsed |