DE838097C

DE838097C - Shaft seal, especially labyrinth seal

Info

Publication number: DE838097C
Application number: DENDAT838097D
Authority: DE
Inventors: Wilhelm Ljungberg Finspong Klas (Schweden)
Original assignee: Svenska Turbmfabnks Aktiebolaget Ljungström, Fmspong (Schweden)
Publication date: 1952-03-27

Description

PatentακSprüche:Patent ακ claims:

1. Wellendichtung, insbesondere Labyrinthdichtung, mit abwechselnd feststehenden und umlaufenden Scheiben, welche eine Welle umschließen, die eine oder mehrere Turbinen- oder Verdichterscheiben trägt, dadurch gekennzeichnet, daß der umlaufende Teil der Wellendichtung mit der danebenliegenden Turbinen- oder Verdicherscheibe axial verriegelt und gegenüber der Welle in axialer Richtung verschiebbar ist.1. Shaft seal, especially labyrinth seal, with alternating fixed and rotating disks that enclose a shaft that carries one or more turbine or compressor disks, characterized in that the circumferential part of the Shaft seal axially locked with the turbine or compressor disk next to it and is displaceable relative to the shaft in the axial direction.

2. Wellendichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Wellendichtung auf einer die Welle umschließenden, gleitbaren Hülse angebracht ist, die mit der Turbinenoder Verdichterscheibe oder einem an dieser befestigten Teil verschraubt oder in anderer Weise, z. B. durch Bajonettverschluß, fest verbunden ist.2. Shaft seal according to claim 1, characterized in that the shaft seal is on a sliding sleeve encompassing the shaft is attached which is connected to the turbine or Compressor disk or screwed to a part attached to it or in another Way, e.g. B. is firmly connected by bayonet lock.

Hierzu 1 Blatt Zeichnungen1 sheet of drawings

5137 4. 525137 4. 52

Claims

The invention relates to shaft seals, in particular labyrinth seals, with alternating fixed and rotating disks, which enclose a shaft, one or more Turbine or compressor disks. The invention is mainly characterized in that that the circumferential part of the shaft seal with the adjacent turbine or Compressor disk locked axially and is displaceable relative to the shaft in the axial direction.

In the drawing, for example, are embodiments of the invention shown. It shows

Fig. Ι a longitudinal section through part of a Radial turbine of known design,

2 shows a longitudinal section through the middle part of a radial turbine with a shaft seal according to the invention,

Fig. 3 is a longitudinal section corresponding to FIG. 2 with a modified embodiment of a Shaft seal according to the invention.

In the drawing, 1 is a turbine shaft on which a turbine disk 2 with blade rings 3 is attached. The propellant is applied to the blade rings through openings 4 in the turbine disk forwarded. The shaft is enclosed by a shaft seal 5. The latter exists made of disks that sit on the shaft, as well as fixed disks arranged in between, which are attached to a wall 6 of a propellant chamber.

To compensate for the axial pressure of the propellant acting on the turbine disk A labyrinth seal 7 is attached to the opposite side of the turbine disk 2. In addition, a thrust bearing 8 is provided to accommodate the unbalanced axial pressures.

The propellant pushes the shaft to the right with a force that is approximately the product of the Pressure times the cross-section of the shaft and half of the shaft seal 5 corresponds. The in modern turbines usually used high pressure, this axial force is for the previously used Camp too high. It must therefore either axial thrust bearings of larger dimensions with consequent higher losses, or the axial pressures must be decreased. The latter can be achieved by attaching the labyrinth seal 7 in such a way that that the disc 2 receives a strong, leftward axial pressure. But then it does exist the possibility that the turbine disk 2 is lifted from the conical shaft end and begins to press on a fastening screw 9 axially mounted in the shaft. if this screw exposed to great stresses at the high temperatures used the material begins to migrate, as a result of which the disk is completely separated from the shaft can.

The aim of the invention is to address this disadvantage by appropriately designing the shaft seal eliminate or reduce.

The shaft seal 5 is subject to an axial pressure directed to the right. As from Fig. 1 it can be seen, this pressure has so far been taken up by the shaft ι via a collar 10, against which the seal is pressed. When this pressure is balanced by the labyrinth seal 7 is to be, the shaft must be subject to a pressure directed to the left, and the force can, As already mentioned above, additional stresses on the fastening screw 9 to Have consequence. According to the invention, the shaft is supported by the axial pressure of the shaft seal 5 relieved by the fact that this pressure is directed to the turbine disk, whereby the fastening screw 9 is relieved of the aforementioned stresses.

2 and 3 of the drawing show two embodiments in which the peripheral part of the Shaft seal 5 is mounted on a shaft enclosing the slidable sleeve 11, which with the Disc 2 can be firmly connected in any way. According to Fig. 2 of the drawing, the sleeve directly connected by thread to the disk, while in the embodiment according to FIG. 3 the sleeve is screwed to a ring 12 which is fastened to the turbine disk by means of bolts is. Instead of a threaded fastening of the sleeve, a bayonet lock can also be used.