SU1420190A1 - Partial turbine - Google Patents

Abstract

The invention allows to increase the efficiency of the turbine. A guide device 2 with nozzle channels 3 and a rotor evenly spaced around the circumference is mounted in the turbine housing. On the rotor of the relay, apparatus 2 has a diaphragm Y installed with sector windows 8. Windows 8 are located opposite the interscapular channels 6 of the disk 5, with which the rotor is equipped. Windows 8 are equipped with nozzle vanes. Due to this turbine design, the working fluid constantly passes through the interscapular ducts .6 regardless of their circumferential position, the thermal overload increases, balancing of the rotor is facilitated, losses from the impact of the flow coming out of the channels 3, on the part of the disc 5. are prevented.

Description

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The invention relates to gas turbine construction, in particular, to the design of partial low flow turbines.

The purpose of the invention is to increase the efficiency of the partial turbine.

FIG. 1 shows a partial turbine; in fig. 2 - reamer sweep of a partial turbine; in fig. 3 is a section A-A in FIG. one.

The partial turbine comprises a housing 1, a guiding device 2 installed therein with uniformly arranged circumferentially nozzle channels 3 and a rotor 4 equipped with a disk 5 and inter-blade channels 6 made on its part. The turbine is provided with a diaphragm 7 mounted on the rotor 15 4 in front of the guide device 2 with sector windows 8 located opposite the interscapular channels 6 of the disk 5. Sector windows 8 are equipped with nozzle vanes 9.

The partial turbine operates as follows.

The working fluid, which is fed to the entrance of the stage through the pie windows 8 of the diaphragm 7, enters the guiding apparatus 2 and

There are nozzle channels 3 located around the entire circumference, and the inlet ports 8 are located opposite the interscapular channels of the disk 5, then the working body constantly passes through the interscapular channels 6 regardless of their circumferential position. The nozzle vanes 9 increase the thermal overload, and evenly distributing the sectors of the inlet ports and interblade channels 6 around the circumference facilitates the balancing of the rotor 4. In addition, losses from the impact of the flow coming from the nozzle channels 3 on the non-flared portion of the disk 5 are prevented.

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Claims (1)

Invention Formula A partial turbine comprising a housing and a guiding device mounted therein with uniformly circumferential nozzle channels and a rotor equipped with a disc with interscapular channels formed on its part, characterized in that the turbine is fitted with a turbine mounted on the rotor guide vane having passed through the nozzle channels 3, with the 25 diaphragm and sector windows, is located in the interscapular channels 6 of the disk 5. placed opposite the interscapular canals. As the guiding device has 2 disk contents. FIG. 7 A There are nozzle channels 3 located around the entire circumference, and the inlet ports 8 are located opposite the interscapular channels of the disk 5, then the working body constantly passes through the interscapular channels 6 regardless of their circumferential position. The nozzle vanes 9 increase the thermal overload, and evenly distributing the sectors of the inlet ports and interblade channels 6 around the circumference facilitates the balancing of the rotor 4. In addition, losses from the impact of the flow coming from the nozzle channels 3 on the non-flared portion of the disk 5 are prevented. Invention Formula A partial turbine comprising a housing and a guiding device mounted therein with uniformly circumferential nozzle channels and a rotor equipped with a disc with interscapular channels formed on its part, characterized in that the turbine is fitted with a turbine mounted on the rotor guide vane diaphragm and sector windows located opposite the interscapular canal-A Fig.Z