US3750983A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine ducted fan engines for aircraft
Assignee: Rolls Royce PLC
•
Filing: 1971-08-09
•
Granted: 1973-08-07
•
Expires: 1991-08-09
Abstract
Abstract In a ducted fan gas turbine engine that part of the fan duct outer wall which extends over the tips of the fan blades, is connected to inter alia the fan air intake in a non-load bearing manner and is thus unaffected by way of deformation when the fan air intake is acted upon by adverse wind conditions. Thus, fouling of the fan blades is avoided. Moreover the fan intake outer wall can be made from relatively light materials.
Inventors
- 👤 G Morris
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 21:21
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/20; B; B64; B64D; B64D27/00; B64D27/02; B64D27/16; B64D27/18; B64D27/40; B64D27/402; B64D27/404; B64D27/406; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
180 words
In combination with aircraft structure, an arrangement for mounting a gas turbine ducted fan engine from the aircraft structure comprising: a gas generator core engine having a casing, a streamlined cowl surrounding said core engine and spaced from the casing thereof, an annular duct between said core engine and said cowl and having an inner wall and an outer wall, a stage of fan blades mounted on the upstream end of said core engine for accelerating air through said duct, suspension means for suspending said core engine from said aircraft structure, at least one cylindrical member rigidly supported By said core engine and forming a portion of said outer wall of said annular duct, said outer wall having a remaining portion formed by said cowl, said cylindrical member being positioned radially outwardly of and around said stage of fan blades, and means for mounting said cowl on said aircraft structure independently of said core engine and said at least one cylindrical member whereby any deformation of the cowl during operation does not interfere with the tips of said fan blades.
Claim 2
Dependent Claim
180 words
In combination with aircraft structure, an arrangement for mounting a gas turbine ducted fan engine from the aircraft structure comprising: a gas generator core engine having a casing, a streamlined cowl surrounding said core engine and spaced from the casing thereof, an annular duct between said core engine and said cowl and having an inner wall and an outer wall, a stage of fan blades mounted on the upstream end of said core engine for accelerating air through said duct, suspension means for suspending said core engine from said aircraft structure, at least one cylindrical member rigidly supported By said core engine and forming a portion of said outer wall of said annular duct, said outer wall having a remaining portion formed by said cowl, said cylindrical member being positioned radially outwardly of and around said stage of fan blades, and means for mounting said cowl on said aircraft structure independently of said core engine and said at least one cylindrical member whereby any deformation of the cowl during operation does not interfere with the tips of said fan blades.
Claim 3
Dependent Claim
48 words
The combination as claimed in claim 1 including means to articulately fix said streamlined cowl at a point downstream of its mid length to said aircraft structure, and in which resilient means support said streamlined cowl at positions upstream of its mid length operatively on said core engine.
Claim 4
Dependent Claim
25 words
The combination as claimed in claim 2 in which said means for articulately fixing said cowl to said aircraft structure is a ball joint means.
Claim 5
Dependent Claim
19 words
The combination as claimed in claim 2 in which said resilient support means comprises a link and boss arrangement.
Claim 6
Dependent Claim
19 words
The combination as claimed in claim 2 including anti rotation links further connecting said cowl to said aircraft structure.
Claim 7
Dependent Claim
16 words
The combination as claimed in claim 1 in which said aircraft structure comprises a rigid beam.
Claim 8
Dependent Claim
15 words
The combination as claimed in claim 6 in which said rigid beam is a pylon.
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) | 1976-08-06 | 1977-02-05 | 1977-08-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-08-06 | 1981-02-05 | 1981-08-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-08-06 | 1985-02-05 | 1985-08-07 | $7700.00 | Window Closed / Lapsed |