Adjusting mechanism for guide blades of turbo-propulsion units

Claim 2

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

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

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

An adjusting mechanism according to claim 3, wherein the structural part consists of at least two ring segments connected with each other.

Claim 6

An adjusting mechanism according to claim 3, wherein the structural part consists of several ring segments connected with each other.

Claim 7

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

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

An adjusting mechanism according to claim 11, wherein the structural part consists of at least two ring segments connected with each other.

Claim 10

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

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

An adjusting mechanism according to claim 9, wherein the slide block guide means are each substantially radially directed.

Claim 13

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.