DE102009054007A1 - Gas turbine i.e. flight gas turbine, for engine of e.g. jet, has circular seal element including outer ring at axial side and thread at opposite axial side, where thread of circular seal element is screwed on thread of high pressure shaft - Google Patents

Abstract

The turbine has a high pressure shaft (4) and a low pressure shaft (7) that is concentrically supported in the high pressure shaft. A hydraulic seal (6) is arranged in an area of a bearing chamber (16), and includes a circular seal element (1), which exhibits an outer ring (8) at an axial side, and is provided with a thread at an opposite axial side, where the thread is screwed on a thread of the high pressure shaft. The seal element is formed for applying axial pre-tensioning force on additional axle components (2, 3).

Description

The invention relates to a gas turbine according to the preamble of claim 1.

In detail, the invention relates to a gas turbine in two- or three-shaft configuration, wherein the gas turbine is designed in particular in the form of an aircraft gas turbine or a jet engine.

From the prior art it is known to arrange a hydraulic seal as an intermediate shaft seal in an intermediate region between shafts. In such seals, the entire assembly is in rotation in the operating state, for example, the inner ring rotates at the speed of a low pressure shaft, while the outer ring rotates at the speed of a high pressure shaft. By centrifugal forces oil is forced radially outward in the sealing area, in order to effect a seal against air passage in this way.

Furthermore, it is known in aircraft engines to fix components, for example bearings by means of shaft nuts on shafts and to connect shafts with each other.

In the prior art, it proves to be disadvantageous that the individual components require a large space and that results in a large number of parts, which in turn increase both the manufacturing costs and installation costs and the weight.

The invention has for its object to provide a gas turbine of the type mentioned, which has a simple design and simple, inexpensive to manufacture a compact design and is provided with a low weight.

According to the invention the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.

According to the invention, it is thus provided that the hydraulic seal comprises an annular sealing element which comprises on one axial side an outer ring of the hydraulic seal and which is provided on its opposite axial side with a thread which can be screwed onto a thread of the high-pressure shaft.

According to the invention a functional combination is thus realized in the smallest space, with which on the one hand, a hydraulic seal can be constructed and with which on the other axial securing of components is possible.

The invention has a number of significant advantages. On the one hand, a compact design is possible, which considerably reduces the volume of construction. Furthermore, there is a reduced number of parts, which in turn leads to a reduction in weight. Overall, significantly reduced production costs, u. a. due to the reduced number of parts needed.

Another advantage results from the fact that certain embodiments of bearing chambers are made possible with hydraulic seals, which are not possible according to the embodiments of the prior art. As a result, the sealing air consumption can be reduced. As a consequence, this also leads to a reduction in fuel consumption.

The solution according to the invention thus provides an integral combination of different functionalities, namely the sealing of waves against each other and the attachment of shafts together.

It is particularly advantageous if the sealing element is designed to apply an axial prestressing force to further axis components. For this purpose, it is advantageous if the sealing element is provided on an axial end face with means for applying a torque, for example a toothing or similar form-fitting embodiments.

Furthermore, it is advantageous if the sealing element is provided with at least one recess for introducing a securing element in order to prevent undesired loosening during operation by axial rotation.

For mounting, it may further be favorable if the outer ring of the hydraulic seal is connected in one piece with the sealing element by a joining method, for example by a welding method.

In the following the invention will be described by means of an embodiment in conjunction with the drawing. Showing:

1 a schematic axial view of a portion of a gas turbine with the sealing element according to the invention, and

2 an enlarged detail view of the illustration according to 1 ,

The figures show a sealing element (sealing ring) 1 , which at its one end face (right side according to 2 ) with a thread 19 which is on a thread 20 a high pressure shaft 4 can be screwed on. This is a circlip 5 interposed. By screwing on the sealing element 1 on the high pressure shaft 4 It is possible, for example, a gear 3 axially secure and / or a bearing 2 to hold in its axial position and fixed to the high pressure shaft 4 a jet engine (gas turbine) to connect.

The deformable circlip 5 has at least one tab 12 on which is in a recess 13 of the sealing element 1 can be introduced to prevent axial rotation.

A hydraulic seal (intermediate shaft seal) 6 prevents the penetration of hot gas into an area 16 , Hot gas is located between a low pressure wave 7 and the high pressure shaft 4 in the area 15 , Thus, a seal of a storage chamber 16 ,

In the hydraulic seal 6 there is always a defined oil volume 14 which is in an outer ring 8th the hydraulic seal 6 held by centrifugal forces during rotation) and by an inner ring 9 is going through. The outer ring 8th rotates at the speed of the high pressure shaft 4 while the inner ring 9 with the speed of the low pressure shaft 7 rotates.

The hydraulic seal further comprises a piston ring 10 as known in the art.

A gearing 11 on the outer ring 8th allows the application of a fastening torque for fixing the components, such as the gear 3 as well as the camp 2 on the high pressure shaft 4 ,

The inner ring 9 is used together with other, unspecified components of the low pressure wave 7 attached to this in a conventional manner.

The outer ring 8th is by means of a welding process via a weld (joint) 18 with the sealing element 1 connected.

The reference number 17 in 1 shows a machine axis.

LIST OF REFERENCE NUMBERS

1

Sealing element / sealing ring

2

camp

3

gear

4

High pressure shaft

5

circlip

6

Hydraulic seal / intermediate shaft seal

7

Low pressure shaft

8th

outer ring

9

inner ring

10

piston ring

11

gearing

12

flap

13

recess

14

oil Capacity

15

Section / annular gap

16

storage chamber

17

machine axis

18

Joint / weld

19, 20

thread

Claims (6)

Gas turbine with a high pressure shaft ( 4 ) and a concentric in this stored low-pressure wave ( 7 ) and one in an area of a storage chamber ( 16 ) arranged hydraulic seal ( 6 ), characterized in that the hydraulic seal ( 6 ) an annular sealing element ( 1 ), which on one axial side an outer ring ( 8th ) and which at the opposite axial side with a thread ( 19 ), which on a thread ( 20 ) of the high pressure shaft ( 4 ) can be screwed on. Gas turbine according to claim 1, characterized in that the sealing element ( 1 ) for applying an axial preload force to further axis components ( 2 . 3 ) is trained. Gas turbine according to claim 1 or 2, characterized in that the outer ring ( 8th ) by joining ( 18 ) in one piece with the sealing ring ( 1 ) connected is. Gas turbine according to claim 3, characterized in that the outer ring ( 8th ) with the sealing element ( 1 ) is welded. Gas turbine according to one of claims 1 to 4, characterized in that the sealing ring ( 1 ) on an axial end face with means ( 11 ) is provided for applying a torque. Gas turbine according to one of claims 1 to 5, characterized in that the sealing ring ( 1 ) with at least one recess ( 13 ) to Insertion of an anti-rotation element ( 5 . 12 ) is provided.

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