Motoren- Und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Munchen Gmbh

Ludwig Schweikl

Friedrich Sippel

Horst Weiss

Christian Greune

Olaf Krauss

Paul Lottes

Two rotationally symmetrically correlated components of a turbomachine, such as a gas turbine engine, define between them an air duct surrounding the axis of the components. A resilient band-like wall section extending radially from the first component bears resiliently in an axial direction against a wall section projecting radially from the second component to provide a seal for the duct. Another wall section of each component cooperate to form a radially extending tongue-in-groove joint, which may incorporate another seal for the duct, this joint permitting relative axial and radial movements between the two components. Means may be provided to maintain the fluid pressure within the duct higher than the pressure exterior thereto. The two components may be joined together by a bayonet-type connection. One of the components may comprise two members so that the member carrying part of the bayonet-type connection can be rotated with respect to the other member during assembly of the two components. One of the components may form part of the turbine casing or part of a turbine nozzle, the cooling channels of the nozzle vanes communicating with the air duct. At least some of the abuting surfaces of the cooperating wall sections may be provided with abraidable coatings, and some may be provided with wear-inhibiting coatings.

Arrangement for joining two relatively rotatable turbomachine components

A liquid reservoir, such as an oil tank, for use in missiles or aircraft which are subjected to extreme flight attitudes. The reservoir has a wall rotationally symmetrical about the longitudinal axis of the reservoir, and the liquid content of the reservoir is rotated about the longitudinal axis to provide, by centrifugal force, a central space within the reservoir which is essentially free of liquid. Air is vented from the reservoir through a fixed vent located within the central space created when the liquid content is rotated.

Vented liquid reservoir

A turbine nozzle vane suspension arrangement of the type wherein the nozzle vanes are suspended by their outer shroud segments from the outer turbine casing and are suspended by their vane ring segments from an annular vane carrier. The vane carrier has axially spaced apart and radially-extending wall sections cooperating with root-ends projecting radially from the vane ring segments. The vane ring segments and their root-ends, and the vane carrier and its wall sections define between them an annular channel for receiving cooling air. The forward wall section of the vane carrier is axially resilient and bears resiliently against the forward vane root-end to provide a seal for the annular channel. The resilient forward wall section can be flexed axially rearwardly to permit the vane ring segments to be mounted on the vane carrier. Seals are provided between the cooperating wall sections and root-ends, or at least some of the contacting surfaces of the wall sections and root-ends are provided with wear-inhibiting and abraidable coatings.

Turbine nozzle vane suspension for gas turbine engines

A jet pipe arrangement is provided for the propulsion and control of an aircraft, which arrangement includes a first stationary pipe section which has a second pipe section fitted with a thrust nozzle attached thereto. To facilitate a simply constructed and operated control arrangement for rotatably moving the second pipe section with respect to the first pipe section, two pairs of angle levers are disposed about the circumference of the first pipe section. The first pair of angle levers are located opposite one another on the first pipe section and have pivot fulcrums located in the plane parallel to the vertical pivot axis of the second pipe section. The second pair of angle levers are likewise located at respective opposite sides on the circumference of the first pipe section and include pivot fulcrums located in a plane parallel to the horizontal pivot axis of the second pipe section. With this arrangement of the angle levers, it is possible to selectively pivot the second pipe section about either or both of the horizontal and vertical pivot axes. To accommodate shifting of the effective rotational or pivot axes of the second pipe section, compensating linkages are also provided between the angle levers and the respective pipe sections.

Jet pipe arrangement for aircraft propulsion and control

An exhaust section of a reaction engine, especially for aircraft, including a fixed pipe and a nozzle pipe carried by the fixed pipe. Pins project from each pipe into slots in the other pipe, and each of a plurality of actuating elements extends between, and is pivoted to, the exteriors of both pipes. The actuating elements are adjustable lengthwise to pivot the nozzle pipe with respect to the fixed pipe. There may be four pairs of pins and slots, and four actuating elements. Each actuating element may include two cooperating actuating members, one of the members being pivoted to the fixed pipe and the other member being pivoted to the nozzle pipe. The actuating members may be a hydraulic piston/cylinder device or a threaded spindle and nut arrangement. Means are provided for operating the actuating elements of each diametrically-opposed pair in opposite directions. The pins and slots may be carried by supporting arms projecting longitudinally from the pipes.

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Moosburg, Germany

Ludwig Schweikl