Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Edouard Sloutski

Alexander Anatolievich Khanin

Sergey Vorontsov

Alexander Ralph Beeck

Remigi Tschuor

Arkadi Fokine

Alexander Burmistrov

Andrey Petrovich Morozov

Anton Sumin

Emil Anner

Alexandre Tchekanov

Andrey Morozov

A cast turbine blade is disclosed and includes an internal cooling passage that passes (e.g., zig-zags or meanders) through the blade from an inlet in the blade root to an outlet in the blade tip. The cooling passage can have a zone at a bend that is at a distance which is remote from the inlet of the cooling passage when the distance from the inlet is measured around the passage, but that is closer to the inlet when the distance from the inlet is measured in a straight line. During casting of the blade, the cooling passage can be defined by a core or cores having a leachable material, the cores being removed after casting by a chemical leaching process. A supplementary passage is also provided for connecting the remote zone to the inlet during the leaching process. The supplementary passage can likewise be defined by a leachable core, or it may be machined into the blade after casting. During the service life of the blade, a plug can be used to obturate the supplementary passage to prevent leakage of cooling air from the cooling passage through the supplementary passage.

Turbine blades

A stator heat shield () for a gas turbine () includes an outside () which in the installed state faces a hot gas path () of the gas turbine (), and an inside () facing away from the outside (). A plurality of ribs () are formed on the inside () and extend axially in the installed state with regard to an axis of rotation () of a rotor () of the gas turbine () and, in the circumferential direction, are spaced a distance apart from one another. At least one baffle plate () is arranged on the inside () and is in contact with the ribs (). At least one groove () is designed in an end face () bordering the stator heat shield () in the circumferential direction, into which at least one sealing element () can be inserted. A plurality of bores () are included, each opening at a distance from the groove () in the direction of the outside () at the inside () at one end and on the end face () at the other end and arranged a distance apart from one another in the axial direction.

Stator heat shield

A heat accumulation segment for local separation of a flow duct inside a turbo engine, from a stator housing that radially surrounds the flow duct is provided. The heat accumulation segment includes two axially opposed joining contoured elements that are engagable with two components that are axially adjacent along the flow duct. A first one of the two joining contoured elements has a radially oriented recess with a contoured surface against which a securing pin having an external contour complementary to the contoured surface acts radially under force action from a component that adjoins the first joining contoured element. The first joining contoured element has a collar portion having radially upper and lower collar surfaces, and the collar portion is connected within a counter-contoured receiving contoured element in the axially adjacent component by a joining force that acts between the securing pin and the conical contoured surface.

Heat accumulation segment

A heat shield arrangement for local separation of a flow channel within a turbine engine, with respect to a stator housing radially surrounding the flow channel is provided. The heat shield includes two axially opposite joining contours which are each engageable with two components which are axially adjacent along the flow channel. Each provides a complementary reception contour for the joining contours. At least one of the reception contours has an axial clearance, in which the associated joining contour is axially displaceably mounted. At least one seal is provided between the axially displaceable joining contour and the reception contour. The seal is mounted movably within the reception contour or the joining contour in such a way that the seal is deflectable against a surface region of the reception contour or of the joining contour.

Heat shield for sealing a flow channel of a turbine engine

A heat accumulation segment for local separation of a flow duct inside a turbo engine, from a stator housing that radially surrounds the flow duct is provided. The heat accumulation segment includes two axially opposed joining contoured elements that are engageable with two components that are axially adjacent along the flow duct. A first one of the two joining contoured elements has a radially oriented recess with a frustoconical contoured surface against which a securing pin having a frustoconical external contour that acts radially under force action from a component that adjoins the first joining contoured element, and the first joining contoured element has a collar portion having a radially upper collar surface and a radially lower collar surface. The collar portion is connected within a counter-contoured receiving contoured element in the axially adjacent component by a joining force that acts between the securing pin and the frustoconical contoured surface.

A rotor blade () for a flow machine includes an aerodynamic blade () and a foot (). The foot () has an anchoring section () on a side facing away from the blade (). A rotor () of the flow machine has an axial anchoring groove () which is complementary to the anchoring section (). The anchoring section () can be inserted axially into the anchoring groove () in order to radially attach the rotor blade () to the rotor (). At least one pulling-off contour () is formed on the foot (), via which an axial pulling-off force can be introduced into the rotor blade (), which is attached to the rotor () with the aid of a pulling-off tool () which is complementary to this pulling-off contour ().

Rotor blade for a flow machine, and an associated pulling-off tool

The invention relates to a gap seal () for sealing a gap () between two adjacent components (), in particular of turbo machines, with the following characteristics:

Growing community of inventors

Moscow, Russia

Edouard Sloutski