US3673802A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fan engine with counter rotating geared core booster
Assignee: General Electric Co
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Filing: 1970-06-18
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Granted: 1972-07-04
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Expires: 1990-06-18
Abstract
Abstract The disclosure describes a turbofan engine having high and low pressure compressors wherein the low pressure compressor, or booster, comprises two counter rotating elements, a rotating duct which carries fan blades on its exterior surface and compressor blades on its interior surface and a conventional compressor rotor which rotates in a direction counter to the direction of rotation of the rotating duct. Alternative gearing schemes for coupling the rotation of the fan to the rotation of the low pressure compressor are shown.
Inventors
- 👤 James Norton Krebs
- 👤 Peter G Kappus
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 22:12
CPC Classifications
F; F02; F02C; F02C3/00; F02C3/04; F02C3/107; F02C3/06; F02C3/067; F02K; F02K3/00; F02K3/02; F02K3/04; F02K3/06
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
155 words
A gas turbine engine comprising inner and outer concentric annular ducts respectively defining primary and secOndary flow paths for discharge of pressurized fluid streams from nozzle means; said inner duct having, in series flow relationship, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine and a low pressure turbine; a first rotor having mounted thereon bladed elements of the high pressure compressor and bladed elements of the high pressure turbine; a second rotor having mounted thereon bladed elements of the low pressure compressor and fan blades projecting into the outer duct to pressurize air flow therethrough; a third rotor having other bladed elements of the low pressure compressor mounted thereon; one of the two rotors consisting of the second and third rotors having bladed elements of the low pressure turbine mounted thereon; and gearing means transmitting power between said second and third rotors and rotating said rotors in opposite directions.
Claim 2
Dependent Claim
155 words
A gas turbine engine comprising inner and outer concentric annular ducts respectively defining primary and secOndary flow paths for discharge of pressurized fluid streams from nozzle means; said inner duct having, in series flow relationship, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine and a low pressure turbine; a first rotor having mounted thereon bladed elements of the high pressure compressor and bladed elements of the high pressure turbine; a second rotor having mounted thereon bladed elements of the low pressure compressor and fan blades projecting into the outer duct to pressurize air flow therethrough; a third rotor having other bladed elements of the low pressure compressor mounted thereon; one of the two rotors consisting of the second and third rotors having bladed elements of the low pressure turbine mounted thereon; and gearing means transmitting power between said second and third rotors and rotating said rotors in opposite directions.
Claim 3
Dependent Claim
50 words
A gas turbine engine as in claim 1 wherein a portion of the inner duct, defining the outer bounds of the primary flow path, is connected to the second rotor adjacent the hub portions of the fan blades and low pressure compressor blades project inwardly of said inner duct portion.
Claim 4
Dependent Claim
54 words
A gas turbine engine as in claim 2 wherein the bladed elements of the low pressure turbine are connected to the second rotor and the third rotor is driven by said second rotor through said gearing means, and said gear means drive the third rotor at a higher rotational speed than the second rotor.
Claim 5
Dependent Claim
62 words
A gas turbine engine as in claim 3 wherein said inner duct portion extends downstream of said fan blades, static structure extends between said low and high pressure compressors and underlies said third rotor, said third rotor is relatively short and is journaled on said underlying static structure and said gear means is supported on the forward end of said static structure.
Claim 6
Dependent Claim
48 words
A gas turbine engine as in claim 3 wherein said inner duct portion extends upstream of said fan blades the third rotor is journaled on the forward end of said second rotor, and the bladed elements of the low pressure compressor are disposed upstream of the fan blades.
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) | 1975-07-04 | 1976-01-03 | 1976-07-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-07-04 | 1980-01-03 | 1980-07-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-07-04 | 1984-01-03 | 1984-07-04 | $7700.00 | Window Closed / Lapsed |