DE102009011879A1 - Integrally bladed rotor and method of making an integrally bladed rotor - Google Patents

Abstract

The invention relates to an integrally bladed rotor (10) for a turbomachine, in particular for a gas turbine, having a rotor main body (12), in the radial edge region of which discharge openings (28) extending in the axial direction are provided. In each relief opening (28), a sealing element (30) is provided, which seals the discharge opening (28) in the radial direction.

Description

The The invention relates to an integrally bladed rotor for a turbomachine, especially for a gas turbine, and a method of making an integral bladed rotor.

Gas turbine rotors with integral blading one designates depending on whether one in the cross section disc-shaped or a cross-sectionally annular Rotor or rotor carrier (hereinafter rotor body) called) is present, as Blisk or Bling. Blisk is the short form from Bladed Disk and Bling from Bladed Ring.

Out In the prior art it is known gas turbine rotors with integral Blading through milling to produce from the full, which of course very expensive and expensive which is why this method is used only for relatively small gas turbine rotors has found. Another, used in large rotors application Method is friction welding one of separately prepared, in particular monocrystalline blades on a particular polycrystalline rotor main body. To high to avoid thermal stresses in the rotor body are in Radial edge region in the axial direction extending discharge openings or slots introduced. So no fluidic disadvantages due to the discharge openings occur, are sealing rings or sealing discs in front of or behind the Rotor arranged, whereby the relief openings or slots are sealed. Such seals or discs are expensive to manufacture and thus expensive and increase the weight of the rotor.

task the invention is to provide an integrally bladed rotor, in which a seal of the discharge openings cost and is realized with low weight, as well as a simple manufacturing process such an integrally bladed rotor.

The Task is bladed integrally by an inventive Rotor for a turbomachine, especially for a gas turbine, solved. The rotor comprises a rotor main body, in its radial edge region are provided in the axial direction extending discharge openings. In every discharge opening a sealing element is provided which the relief opening in seals in the axial direction. This way will not be separate Sealing rings or discs needed, which saves weight. Since a sealing element associated with only one discharge opening simplifies the construction of the sealing elements, thereby reducing costs be saved.

Preferably have the sealing elements on a stop, with which they on a Abut the end face of the rotor. This way, a simple Positioning of the sealing elements and a simple attachment on the rotor allows.

The Sealing elements can have at least one bending extension on one end face of the rotor is applied. Thus, the sealing elements by bending attached to the bending extension of the rotor.

According to one preferred embodiment lie the sealing elements as dampers between adjacent blade necks. this makes possible an improved damping of vibrations of the rotor.

Preferably each of the sealing elements has a sealing plate which is connected to the Cross section of the discharge opening is adjusted. The sealing plate allows for optimal sealing the discharge opening.

The Sealing plate leaves to act like this that the thickness of the sealing plate by at least a factor of 5 less is as the length the discharge opening. This allows a further saving of weight in the radial edge area of the Rotor base.

Preferably the sealing plate lies in the relief opening. In this way takes the sealing plate no additional Space available.

The Sealing plate is, for example, in the axial direction substantially in the middle of the discharge opening intended. So the seal of the discharge opening remains obtained in small displacements of the sealing plate in the axial direction.

According to one another embodiment each of the sealing elements has two sealing plates. This allows a improved sealing of the discharge opening.

Preferably the two sealing plates of the sealing elements are arranged so that they at the two ends of the discharge opening with the front sides of the rotor form a plane in the area of the discharge openings, d. H. flush to lock. In this way, only slight results in rotation of the rotor Ventilation losses in the area of the discharge openings.

According to one another embodiment are sealing elements provided with different masses. This allows a Balancing the rotor by means of the sealing elements.

Preferably, the sealing elements ei NEN radially outer web, which has at least one protruding from the web sealing plate and at both ends of the web stops, wherein the stops preferably engage the end faces of the rotor. In this way, the sealing element is attached via the two stops at the ends on the end faces of the rotor, whereby slipping of the sealing plate is prevented. These attacks are z. B. a permanent extension and a bending extension.

The Invention relates to this In addition, a method of manufacturing an integrally bladed rotor with the following process steps. In a first step the attachment of blades to a rotor body, wherein in the radial edge region of the rotor body discharge openings are provided, which lie in the region of slots of adjacent blade necks. In a second step, the discharge openings are closed by sealing elements. this makes possible a simple manufacture of the rotor, being expensive to produce and heavy sealing rings or discs can be dispensed with, thereby Weight and costs are saved.

at In another variant of the method, the balancing of the rotor takes place by means of different heavy sealing elements. This makes possible, the sealing of the discharge openings and to perform the balancing of the rotor in one method step.

Further Features and advantages of the invention will become apparent from the following Description and from the following drawings, to the reference is taken. In the drawings show:

1 a perspective view of an integrally bladed rotor according to a first embodiment of the invention;

2 a detailed view of a sealing element according to the in 1 embodiment shown;

3 a plan view of the end face of in 1 shown rotor;

4 a sectional view along the in 3 shown section plane IV-IV;

5 a perspective view of an integrally bladed rotor according to a second embodiment of the invention;

6 a detailed view of a sealing element according to the in 5 embodiment shown;

7 a plan view of the end face of in 5 shown rotor; and

8th a sectional view along the in 7 shown section plane VIII-VIII.

A first embodiment of the invention will be described with reference to 1 to 4 described. An integrally bladed rotor 10 has a rotor body 12 on, which is a rotor disk in the embodiment shown. The rotor body 12 but may also be annular, for example.

The integrally bladed rotor 10 is designed for a gas turbine, wherein it may be arranged in the turbine section or in the compressor section. Of course, the invention can also be applied to integrally bladed rotors of other turbomachines.

At the outer radius of the rotor body 12 are several shovels 14 provided, which in the embodiment shown via separate spacers 16 with the rotor body 12 are connected.

A shovel 14 is constructed as follows: radially inward is a blade neck 18 provided, from the blade neck 18 extends the airfoil 20 radially outward. At the outer end of the airfoil 20 is an outer shroud 22 intended.

The shovels 14 For example, they are made of single-crystalline nickel-based materials that do not allow fusion welding. Such a shovel 14 is first by friction welding, in particular linear friction welding, with an intermediate piece 16 connected. The intermediate piece 16 is made of a different material than the blade 14 made, for example, of a polycrystalline material. The shovel 14 can then over the intermediate piece 16 using various methods on the rotor body 12 be attached. Of course it is also possible that the blades 14 with suitable methods directly on the rotor body 12 are attached.

To the weight of the rotor 10 To keep as low as possible, is a lightweight construction for the blade neck 18 intended. In the blade necks 18 are recesses on the sides lying in the circumferential direction 24 provided (cf. 1 and 4 ). Between adjacent blade necks 18 be through the recesses 24 in opposite sides of the blade necks 18 Cavities formed.

The blade necks 18 each have a in axial direction front and rear extension on. The extensions together form a running in the circumferential direction inner shroud 26 ,

In the radially outer edge region of the rotor base body 12 are axially extending discharge openings 28 intended. The relief openings 28 serve, for example, to reduce stresses in the rotor body 12 due to thermal stresses due to hot gases passing through the turbomachine.

Radially outside the discharge openings 28 are narrow slits 29 between adjacent blade necks 18 provided in the openings 28 pass.

In the relief openings 28 is each a sealing element 30 provided, which is the discharge opening 28 seals in the axial direction.

In the 1 and 3 are some relief holes 28 of the rotor 10 with inserted sealing elements 30 and some relief openings 28 with removed sealing elements 30 shown.

2 shows a detailed view of one of the sealing elements 30 according to a first embodiment of the invention. The sealing element 30 has a radially outer web 32 on. At the left end of the jetty 32 is provided a thickening, which is a first stop 34 which forms at a first end face 36 of the rotor 10 is present (cf. 1 or 4 ).

On the right end of the jetty 32 is a bending process 38 educated. The bending process 38 is after insertion of the sealing element 30 in the discharge opening 28 of the rotor 10 90 ° bent upwards, so that with its upper surface on the second end face 36 of the rotor 10 is applied. Thus forms the bending process 38 in the bent state, a second stop of the sealing element 30 , Of course it is also possible to have one or more bending extensions 38 so on the sealing element 30 to arrange that they can be bent in different directions, for example, laterally.

A sealing plate 40 stands from the jetty 32 downwards. The shape of the sealing plate 40 is at the cross section of the discharge opening 28 adapted to achieve optimum sealing. The sealing plate 40 is essentially in the middle of the radially outer web 32 arranged and is thus in the assembled state within the discharge opening 28 more precisely in the axial direction substantially in the middle of the discharge opening 28 arranged.

The thickness of the sealing plate 40 is at least a factor of 5 less than the length of the discharge opening 28 in the axial direction. This way, in the area of the discharge opening 28 Material saved, thereby reducing the weight of the rotor 10 reduced. For maximum weight saving is the discharge opening 28 as large as possible, without the stability of the rotor 10 is impaired.

When assembled, the sealing element 30 so arranged it with the first stop 34 on the first front side 36 and with a second stop passing through the bent flexure 38 is formed, at the second end face 36 of the rotor 10 is applied, whereby a movement of the sealing element 30 is prevented in the axial direction (see. 4 ).

The radially outer web 32 of the sealing element 30 is a damper between adjacent blade necks 18 , The damper serves in particular to reduce vibrations of the blades 14 , One option to achieve the damping effect is that the top of the web 32 at the top of the discharge opening 28 is applied and is absorbed by friction kinetic energy.

The different sealing elements 30 , each one a discharge opening 28 are assigned, may have different masses, whereby a balancing of the rotor 10 using the sealing elements 30 is possible. The sealing elements 30 additionally serve as balancing masses.

The 5 to 8th show a second embodiment of the invention. The construction of rotor body 12 and shovels 14 are identical to in 1 to 4 shown first embodiment. The second embodiment differs from the first embodiment by an altered sealing element 30 ,

6 shows a detailed view of the sealing element 30 the second embodiment of the rotor 10 , At a radially outer web 32 are two sealing plates 40 attached, each to the cross-section of the discharge opening 28 are adjusted. At the ends of the radially outer web 32 are analogous to the first embodiment, a first stop 34 and a bending process 38 intended.

The arrangement of the sealing elements 30 in the mounted state in the rotor 10 is especially good in 8th to recognize. The sealing element 30 lies with the first stop 34 on the left front side 36 of the rotor 10 on and with the bent bending extension 38 making a second stop, on the right front side 36 of the rotor 10 at.

The two sealing plates 40 the Dichtelemen th 30 are arranged so that they are at the two ends of the discharge opening 28 with the front sides 36 of the rotor 10 form a level or finish flush. This results in rotation of the rotor 10 only low flow losses through the sealing elements 30 ,

As in 8th The bending processes are easy to recognize 38 bent by approximately 180 ° and lie with its end face on the front side 36 of the rotor 10 at. Of course it is also possible, the bending processes 38 analogous to the first embodiment (cf. 4 ) bend only by about 90 ° so that the bending processes 38 with its upper surface at the front 36 of the rotor 10 issue. Similarly, the bending processes 38 The first embodiment may be bent by approximately 180 ° analogously to the second embodiment. It is also conceivable, several bending processes 38 to bend in different directions.

In the following, a method according to the invention for producing an integrally bladed rotor as described above 10 described.

In a first process step, the blades 14 on a rotor body 12 attached. This can be done by various methods, in particular using an intermediate piece 16 to facilitate welding processes. In the radial edge region of the rotor main body 12 are thereby discharge openings 28 provided in the region of slots of adjacent blade necks 18 lie. The relief openings 28 can, for example, in the attachment of individual blades 14 on the rotor body 12 , arise process-related, or they can after attaching the blades 14 on the rotor body 12 , for example, by drilling or milling, arise.

In a second process step, the discharge openings 28 through the sealing elements 30 closed and sealed. These are the sealing elements 30 with the bending process 38 ahead in the discharge openings 28 introduced until the first stop 34 at the front 36 of the rotor 10 is applied. Then the bending process becomes 38 on the other side of the rotor 10 from the discharge opening 28 sticking out, bent upwards until it's at the front 36 of the rotor 10 abuts and thus forms a second stop, whereby the sealing element 30 stuck in the discharge opening 28 is held. The mass of the respective sealing elements 30 is tuned so that simultaneously with the sealing of the discharge openings 28 a balancing of the rotor 10 he follows.

It is also possible that instead of the first stop 34 in the form of a thickening of the sealing element 30 on both sides of the sealing element 30 a bending process 38 is provided, wherein during assembly of the sealing element 30 the bending processes 38 be bent on both sides of the sealing element and in each case at the front side 36 of the rotor 10 abut and make a stop.

Such a sealing element 30 is symmetrical, for example, whereby the orientation of the sealing element 30 does not have to be considered during assembly.

It can also have more than two sealing plates 40 Use, so that a kind of labyrinth seal can result.

10

rotor

12

Rotor body

14

shovel

16

connecting piece

18

scoop-neck

20

airfoil

22

outer shroud

24

recess

26

inner shroud

28

relief opening

29

slot

30

sealing element

32

web

34

attack

36

front

38

Bending extension

40

sealing plate

Claims (14)

Integrally bladed rotor ( 10 ) for a turbomachine, in particular for a gas turbine, with a rotor main body ( 12 ), in the radial edge region extending in the axial direction discharge openings ( 28 ) are provided, characterized in that in each discharge opening ( 28 ) a sealing element ( 30 ) is provided, which the discharge opening ( 28 ) seals in the axial direction. Rotor according to claim 1, characterized in that the sealing element ( 30 ) a stop ( 34 ), with which it at one end face ( 36 ) of the rotor ( 10 ) is present. Rotor according to claim 1 or 2, characterized in that the sealing element ( 30 ) at least one bending extension ( 38 ), which at one end face ( 36 ) of the rotor ( 10 ) is present. Rotor according to one of the preceding claims, characterized in that the density lement ( 30 ) as a damper between adjacent blade necks ( 18 ) lies. Rotor according to one of the preceding claims, characterized in that the sealing elements ( 30 ) each have a sealing plate ( 40 ), which at the cross section of the discharge opening ( 28 ) is adjusted. Rotor according to claim 5, characterized in that the thickness of the sealing plate ( 40 ) is at least a factor of 5 less than the length of the discharge opening ( 28 ). Rotor according to claim 5 or 6, characterized in that the sealing plate ( 40 ) in the discharge opening ( 28 ) lies. Rotor according to one of claims 5 to 7, characterized in that the sealing plate ( 40 ) in the axial direction substantially in the middle of the discharge opening ( 28 ) is provided. Rotor according to one of claims 5 to 7, characterized in that the sealing elements ( 30 ) at least two sealing plates ( 40 ) exhibit. Rotor according to claim 9, characterized in that the sealing plates ( 40 ) of the sealing elements ( 30 ) are arranged so that they at the two ends of the discharge opening ( 28 ) with the end faces ( 36 ) of the rotor ( 10 ) in the area of the discharge openings ( 28 ) form a plane. Rotor according to one of the preceding claims, characterized in that sealing elements ( 30 ) are provided with different masses. Rotor according to one of the preceding claims, characterized in that the sealing elements ( 30 ) a radially outer web ( 32 ) having at least one of the web ( 32 ) protruding sealing plate ( 40 ) and at both ends of the web ( 32 ) Stops, wherein the stops preferably at the end faces ( 36 ) of the rotor ( 10 attack). Method for producing an integrally bladed rotor ( 10 ), characterized by the following process steps: - attachment of blades ( 14 ) on a rotor main body ( 12 ), wherein in the radial edge region of the rotor body ( 12 ) Discharge openings ( 28 ) are provided in the region of slots of adjacent blade necks ( 18 ) lie; - closing the discharge openings ( 28 ) by sealing elements ( 30 ). Method according to claim 13, characterized in that balancing of the rotor ( 10 ) by inserting sealing elements ( 30 ) of different weight.