Patent US3668389A successfully refreshed from Google Patents.
US4428189A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Case deflection control in aircraft gas turbine engines
Assignee: RTX Corp
•
Filing: 1980-04-02
•
Granted: 1984-01-31
•
Expires: 2000-04-02
Abstract
Abstract A gas turbine engine and structure for mounting the gas turbine engine on an aircraft is disclosed. Techniques for controlling the magnitude of engine case deflection from the axis of the engine are developed. The transfer of a portion of the gust and thrust loads externally of the engine case to a location downstream of the rearward engine mount generates a reverse moment which counteracts deflection in the engine case.
Inventors
- 👤 Paul B. Greenberg
- 👤 C. Heinz Lenkeit
- 👤 Willard J. Seibert
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 16:01
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/20
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
68 words
An aircraft gas turbine engine of the type having an engine case and including forward mounting means and rearward mounting means for attaching the engine case to the aircraft, wherein the improvement comprises: means external to the engine case and pivotable about the forward mounting means for transferring loads applied about the forward mounting means to a location on the engine case downstream of the second mounting means.
Claim 2
Dependent Claim
68 words
An aircraft gas turbine engine of the type having an engine case and including forward mounting means and rearward mounting means for attaching the engine case to the aircraft, wherein the improvement comprises: means external to the engine case and pivotable about the forward mounting means for transferring loads applied about the forward mounting means to a location on the engine case downstream of the second mounting means.
Claim 3
Dependent Claim
45 words
The invention according to claim 1 wherein said means for transferring said loads to the location downstream of the second mounting means is attached to the engine case upstream of the forward mounting means and to the engine case downstream of the rearward mounting means.
Claim 4
Dependent Claim
43 words
The invention according to claim 2 wherein said means for transferring said loads is pivotable about the forward mounting means to cause downward deflection of the engine case at the downstream point of attachment of the load transferring means to the engine case.
Claim 5
Dependent Claim
131 words
An aircraft gas turbine engine of the turbofan type having a fan section and a core section wherein the core section is circumscribed by an engine case having at the forward end thereof a first mounting means and at the rearward end thereof a second mounting means for attaching the engine case to the aircraft, and having a cowl structure attached at one end to the engine case downstream from the fan section, and pivotable about the forward mounting means wherein the cowl is attached at the other end thereof to the engine case at a location downstream of the second mounting means so as to be capable of resisting case deflection downstream of the second mounting means in response to moments generated by thrust loads about the first mounting means.
Claim 6
Dependent Claim
131 words
An aircraft gas turbine engine of the turbofan type having a fan section and a core section wherein the core section is circumscribed by an engine case having at the forward end thereof a first mounting means and at the rearward end thereof a second mounting means for attaching the engine case to the aircraft, and having a cowl structure attached at one end to the engine case downstream from the fan section, and pivotable about the forward mounting means wherein the cowl is attached at the other end thereof to the engine case at a location downstream of the second mounting means so as to be capable of resisting case deflection downstream of the second mounting means in response to moments generated by thrust loads about the first mounting means.
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) | 1987-01-30 | 1987-08-01 | 1988-01-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-01-30 | 1991-08-01 | 1992-01-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-01-30 | 1995-08-01 | 1996-01-31 | $7700.00 | Window Closed / Lapsed |