Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Hans-Juergen Schmuhl

Gerhard Zaehring

Josef Wohlmuth

Gerhard Wydra

Klemens Werner

Wolfgang Krueger

Lothar Reisinger

Paul Lottes

Dietrich Schulte

Run-on linings for turbo-engines are arranged between the free ends of moving blades and a housing of a compressor or a turbine of a turbo-engine. The run-on linings are formed of a carrier and fiber bundles and are fastened on the circumference of the housing.

Blade tip seal insert

A compressor impeller has a ring-shaped shroud band which is mounted at blade tips, each blade tip being enclosed in an identical radially slidable manner by a guide block, and the guide blocks being fastened to the shroud band. As a result, a narrow sealing gap and thus lower aerodynamic losses can be implemented than in conventional compressors, and the different centrifugally and thermally induced expansions of the blade and of the shroud band can be compensated.

Compressor impeller

The hollow shaft of a high pressure compressor is provided in a conically tapering section downstream of the last rotor disc on its inner surface with a vane-like rib arrangement for conveying a stream of cooling air from the vicinity of the axis of the shaft into the outer peripheral regions of the last rotor disc. The stream then passes through corresponding circumferentially distributed axial holes in the rotor disc. In this way, better cooling of the last compressor stages which have been heated by the main stream of air in the compressor and a reduction in the stresses in the structural parts can be obtained.

Method and apparatus for cooling a high pressure compressor of a gas

The conical section of the hollow shaft of a high pressure compressor behind the last rotor disc is surrounded by an annular protective shield. The shield serves to protect the hollow shaft and the last rotor disc from the main stream of hot compressed air leaving the compressor. Between the hollow shaft and the heat shield a stream of cooling air is furthermore conducted from the vicinity of the axis to the outer region of the last rotor disc. The stream of air then passes through corresponding circumferentially distributed axial holes in the last rotor disc.

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Woerthsee, Germany

Hans-Juergen Schmuhl