Patent US3908362A successfully refreshed from Google Patents.
US3908362A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Bypass turbojet with variable pitch low pressure compressor for thermal load control
Assignee: Individual
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Filing: 1971-04-27
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Granted: 1975-09-30
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Expires: 1991-04-27
Abstract
Abstract A bypass turbojet provided with tachometric fuel metering means for maintaining a constant engine rotation speed, characterized by the fact that a low-pressure compressor has variable-pitch blades for regulating the thrust delivered, variation of the pitch of said variable-pitch blades being controlled by a servomechanism associated to a thermal load limiter operating either as a temperature regulator ahead of the turbine subsequent to presetting of such temperature, or as a limiter in the event of manual control of the pitch of said blades.
Inventors
- 👤 Joseph Szydlowski
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 06:47
CPC Classifications
F; F04; F04D; F04D27/00; F04D27/02; F04D27/0246; F02; F02C; F02C3/00; F02C3/20; F02C3/30; F02C7/00; F02C7/12; F02C7/14; F02C7/141; F02C9/00; F02C9/48; F02C9/56; F02C9/58; F02K; F02K3/00; F02K3/02; F02K3/04; F02K3/06; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
240 words
In a bypass turbojet having a main duct, a bypass duct, a low pressure compressor and a high pressure compressor in series flow with the low pressure compressor and disposed in the main duct, the low pressure compressor additionally feeding the bypass duct and turbine means for actuating the compressors, the improvements which comprise: a. the low pressure compressor having variable pitch blading disposed in both the bypass duct and the main duct; b. tachometric fuel metering means for maintaining a constant rotational speed of the turbine means; c. a servomechanism operatively connected to the variable pitch blading of the low pressure compressor; and d. a thermal load limiter for regulating the temperature ahead of the turbine means and operatively connected to the servomechanism including means responsive to the instantaneous actual fuel flow to the turbine means as compared to the theoretical maximum flow rate which can be admitted to the turbine means and generating a signal proportional thereto, e. means responsive to the signal for automatically reducing the blade pitch as soon and as long as either the actual turbine means temperature or the actual rate of fuel flow tends to exceed its upper limit, f. the means responsive to the signal automatically increasing the blade pitch as soon as either the difference between the actual rate of fuel flow and its lower limit or the fuel feeding in flight for the turbine means tends to a zero valve.
Claim 2
Dependent Claim
240 words
In a bypass turbojet having a main duct, a bypass duct, a low pressure compressor and a high pressure compressor in series flow with the low pressure compressor and disposed in the main duct, the low pressure compressor additionally feeding the bypass duct and turbine means for actuating the compressors, the improvements which comprise: a. the low pressure compressor having variable pitch blading disposed in both the bypass duct and the main duct; b. tachometric fuel metering means for maintaining a constant rotational speed of the turbine means; c. a servomechanism operatively connected to the variable pitch blading of the low pressure compressor; and d. a thermal load limiter for regulating the temperature ahead of the turbine means and operatively connected to the servomechanism including means responsive to the instantaneous actual fuel flow to the turbine means as compared to the theoretical maximum flow rate which can be admitted to the turbine means and generating a signal proportional thereto, e. means responsive to the signal for automatically reducing the blade pitch as soon and as long as either the actual turbine means temperature or the actual rate of fuel flow tends to exceed its upper limit, f. the means responsive to the signal automatically increasing the blade pitch as soon as either the difference between the actual rate of fuel flow and its lower limit or the fuel feeding in flight for the turbine means tends to a zero valve.
Claim 3
Dependent Claim
32 words
A by-pass turbojet according to claim 1, wherein pure water injecting means are disposed downstream of said low pressure compressor in the air stream at the inlet of said high pressure compressor.
Claim 4
Dependent Claim
150 words
A by-pass turbojet according to claim 2, in which said pure water injecting means comprises, in combination: a pure water tank; a reservoir; duct means connected between said pure water tank and said reservoir; a source of compressed air; communication means interconnected between said pure water tank, said reservoir, and said source of compressed air; a lipped member situated upstream of said high pressure compressor and in an inlet of said high pressure compressor; a plurality of nozzles situated in the vicinity of said lipped member; distributing means communicating with said reservoir and said nozzles; and said nozzles being positioned and oriented so that pure water is discharged from said nozzles substantially perpendicular to the direction of the air flowing into said high pressure compressor, and whereby said reservoir is emptied and scavanged, and spray is discharged through said nozzles regularly into the air flowing into said high pressure compressor.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-09-29 | 1979-03-31 | 1979-09-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-09-29 | 1983-03-31 | 1983-09-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-09-29 | 1987-03-31 | 1987-09-30 | $7700.00 | Window Closed / Lapsed |