US4810165A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Adjusting mechanism for guide blades of turbo-propulsion units
Assignee: MTU Aero Engines AG
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Filing: 1987-07-08
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Granted: 1989-03-07
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Expires: 2007-07-08
Abstract
Abstract An adjusting mechanism for pivotal guide blades of turbo-propulsion units in which a rotatable adjusting ring is supported in a concentric support ring. The support ring is heat-insulatingly connected with the turbine housing by way of several connecting lugs or slide block guidances distributed over the circumference and the adjusting ring is connected with the guide blades by way of bendable pivot levers. It is achieved thereby that the heat flow from the hot turbine housing to the adjusting mechanism remains small and an exact adjustment of the guide blades can be achieved in this manner.
Inventors
- 👤 Christian Greune
- 👤 Hilbert Holzhauer
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 17:25
CPC Classifications
F; F01; F01D; F01D17/00; F01D17/10; F01D17/12; F01D17/14; F01D17/16; F01D17/162
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
151 words
An adjusting mechanism for pivotal guide blades of turbo-propulsion units, comprising a turbine housing means, an adjusting ring means located outside of the turbine housing means, a coaxial support ring means, the adjusting ring means being rotatably supported on said support ring means by way of bearing means, bendable pivot levers bendable substantially perpendicularly to the pivot plane and operatively connected with the guide blades, said pivot levers being movably arranged at the adjusting ring means on the blade side thereof, and connecting means connecting the support ring means with the turbine housing means in a heat-insulating manner by way of a plurality of separate connecting elements distributed over the circumference of the turbine housing means, thereby minimizing heat transfer from the turbine housing means to the supporting ring means and adjusting ring means, wherein the connecting elements are connecting lugs formed as separate spaced flat sections of an annular band.
Claim 2
Dependent Claim
151 words
An adjusting mechanism for pivotal guide blades of turbo-propulsion units, comprising a turbine housing means, an adjusting ring means located outside of the turbine housing means, a coaxial support ring means, the adjusting ring means being rotatably supported on said support ring means by way of bearing means, bendable pivot levers bendable substantially perpendicularly to the pivot plane and operatively connected with the guide blades, said pivot levers being movably arranged at the adjusting ring means on the blade side thereof, and connecting means connecting the support ring means with the turbine housing means in a heat-insulating manner by way of a plurality of separate connecting elements distributed over the circumference of the turbine housing means, thereby minimizing heat transfer from the turbine housing means to the supporting ring means and adjusting ring means, wherein the connecting elements are connecting lugs formed as separate spaced flat sections of an annular band.
Claim 3
Dependent Claim
23 words
An adjusting mechanism according to claim 1, wherein the connecting lugs are connected with a fastening ring secured at the turbine housing means.
Claim 4
Dependent Claim
26 words
An adjusting mechanism according to claim 2, wherein the support ring means, the fastening ring and the connecting lugs are constructed as an integral structural part.
Claim 5
Dependent Claim
22 words
An adjusting mechanism according to claim 3, wherein the structural part consists of at least two ring segments connected with each other.
Claim 6
Dependent Claim
20 words
An adjusting mechanism according to claim 3, wherein the structural part consists of several ring segments connected with each other.
Claim 7
Dependent Claim
51 words
An adjusting mechanism according to claim 2, wherein said fastening ring is a substantially flat annular ring and the connecting lugs protrude axially from an edge of a flat annular face of the fastening ring and serve to hold the support ring means at an axial spacing from the fastening ring.
Claim 8
Dependent Claim
26 words
An adjusting mechanism according to claim 6, wherein the support ring means, the fastening ring and the connecting lugs are constructed as an integral structural part.
Claim 9
Dependent Claim
22 words
An adjusting mechanism according to claim 11, wherein the structural part consists of at least two ring segments connected with each other.
Claim 10
Dependent Claim
159 words
An adjusting mechanism, for pivotal guide blades of turbo-propulsion units, comprising a turbine housing means, an adjusting ring means located outside of the turbine housing means, a coaxial support ring means, the adjusting ring means being rotatably supported on said support ring means by way of bearing means, bendable pivot levers bendable substantially perpendicularly to the pivot plane and operatively connected with the guide blades, said pivot levers being movably arranged at the adjusting ring means on the blade side thereof, and connecting means connecting the support ring means with the turbine housing means in a heat-insulating manner by way of a plurality of separate connecting elements distributed over the circumference of the turbine housing means, thereby minimizing heat transfer from the turbine housing means to the supporting ring means and adjusting ring means, wherein the connecting means includes several slide block guide means distributed over the circumference for connecting the support ring means with the turbine housing means.
Claim 11
Dependent Claim
159 words
An adjusting mechanism, for pivotal guide blades of turbo-propulsion units, comprising a turbine housing means, an adjusting ring means located outside of the turbine housing means, a coaxial support ring means, the adjusting ring means being rotatably supported on said support ring means by way of bearing means, bendable pivot levers bendable substantially perpendicularly to the pivot plane and operatively connected with the guide blades, said pivot levers being movably arranged at the adjusting ring means on the blade side thereof, and connecting means connecting the support ring means with the turbine housing means in a heat-insulating manner by way of a plurality of separate connecting elements distributed over the circumference of the turbine housing means, thereby minimizing heat transfer from the turbine housing means to the supporting ring means and adjusting ring means, wherein the connecting means includes several slide block guide means distributed over the circumference for connecting the support ring means with the turbine housing means.
Claim 12
Dependent Claim
18 words
An adjusting mechanism according to claim 9, wherein the slide block guide means are each substantially radially directed.
Claim 13
Dependent Claim
60 words
An adjusting mechanism according to claim 9, wherein pin means are attached to an axial side of the support ring which faces the slide block guide means, said slide block guide means including guide surfaces engageable with the pin means to support the support ring while permitting movement of the support ring in the axial direction of the propulsion unit.
References Cited (Backward Citations)
US2651496A
Cited
GB755527A
Cited
US2933234A
Cited
US2932440A
Cited
DE1108988B
Cited
US2936108A
Cited
US3303992A
Cited
US3652177A
Cited
US3841788A
Cited
US3990809A
Cited
US4035101A
Cited
US4150915A
Cited
US4330234A
Cited
US4363600A
Cited
US4400135A
Cited
US4709546A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1992-03-06 | 1992-09-05 | 1993-03-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-03-06 | 1996-09-05 | 1997-03-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-03-06 | 2000-09-05 | 2001-03-07 | $7700.00 | Window Closed / Lapsed |