Alstom Technology Limited

Microsoft Technology Licensing, LLC

Alexander Burmistrov

Alexander Anatolievich Khanin

Maxim Konter

Jason Andrew Chen

Sergey Vorontsov

Edouard Sloutski

Yekaterina Grabar

Dvir Horovitz

Jyotkumar Jagdishbhai Patel

Chelsea Nicole Mitchell

Nikola Todic

Aleksandar Samardzija

Siddhika Nevrekar

Dzmitry Dulko

Architecture that comprises features that enable smart searches along a route based on time to entities along the route and off the route, a user experience (UX) that showcases rich entities along the route, saving, sharing and editing capabilities across devices and users, smart ranking and filtering of entities, and user preferences and digital personal assistant interaction. After an itinerary is built, the itinerary can be saved for future use and/or shared with friends and/or other devices. Users can change the itinerary on-the-go by searching and adding entities, at a later time, for example. A digital personal audio assistant can be utilized to provide guidance based on the itinerary, and ask users if they want to take a particular exit to visit some desired location (e.g., place of interest).

Search along the route

A gas turbine () includes a rotor () which has two rotor blade rows () with a plurality of rotor blades (), and also a rotor heat shield (), which is arranged between them, with a plurality of heat shield elements (), and with a stator () which has a stator blade row (), with a plurality of stator blades (), which is arranged axially between the two adjacent rotor blade rows (). The stator blades () have a stator sealing structure () radially on the inside. The heat shield elements () have a rotor sealing structure () radially on the outside which interacts with the stator sealing structure () for forming an axial seal (). Furthermore, a blade radial seal () is formed between two adjacent rotor blades (), and also a heat shield radial seal () is formed between two adjacent heat shield elements (), and in each case separates a gas path () from the rotor (). For increasing efficiency, the heat shield elements () and the rotor blades () are matched to each other so that the heat shield radial seal () merges without interruption into the blade radial seals () of the two axially adjacent rotor blades () in such a way that a continuous radial seal () is formed from the one rotor blade (), via the heat shield element (), to the other rotor blade ().

Turbo machine and gas turbine

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

Growing community of inventors

Moscow, Russia

Alexander Burmistrov