WO2021073786A1

WO2021073786A1 - Rotor comprising a rotor component arranged between two rotor discs

Info

Publication number: WO2021073786A1
Application number: PCT/EP2020/066858
Authority: WO
Inventors: Peter Kury; Mirko Milazar; Christopher W ROSS; Yulia Bagaeva; Karsten Kolk; Ivan Lbov; Alexander Romanov; Harald Hoell; Kevin KAMPKA; Rene Mahnke; Andreas Föhrigen; Daniel Hofsommer; Ekkehard Maldfeld; Jörg Richter
Original assignee: Siemens Energy Global GmbH & Co. KG
Priority date: 2019-10-18
Filing date: 2020-06-18
Publication date: 2021-04-22
Also published as: CN114599859A; JP2022552170A; JP7394979B2; EP4013950B1; CN114599859B; EP4013950A1; KR20220078706A

Abstract

The invention relates to a rotor of a gas turbine comprising two adjacent rotor discs (01, 11), on each of which moving blades are fastened, an annular rotor component (21) being arranged between the rotor discs (01, 11) and having at its opposite ends circumferential annular grooves (24, 34), in each of which a circumferential fastening projection (04, 14) on the respective rotor disc (01, 11) engages. According to the invention, when the rotor is stationary a first outer flank (25) of the first annular groove (24) rests under pressure against a first outer flank (05) of the first fastening projection (04) and there is play between a first inner flank (26) of the first annular groove (24) and a first inner flank (06) of the first fastening projection (04).

Description

description

Rotor component with a rotor arranged between two rotor disks

The invention relates to a rotor of a gas turbine which has at least two rotor disks connected to one another, between which an annular rotor component is arranged.

Various designs of rotors for use in gas turbines with interconnected rotor disks are known from the prior art, an annular rotor component for shielding the inner region of the rotor from the hot gas flowing through the gas turbine being arranged between the rotor disks. Here, the two rotor disks each have a plurality of rotor blades distributed around the outer circumference. Between the two rows of rotor blades there is a row with guide vanes distributed around the circumference, each of which is attached to the stationary housing. Because of the rotation of the rotor, there is inevitably a gap between the guide vanes and the rotor blades. This basically allowed hot gas to enter the area radially inside the guide vanes. In order to keep the hot gas away from the inside of the rotor, an annular rotor component is arranged between the two adjacent rotor disks in some gas turbines. For this purpose, this rotor component is mounted on both sides of the rotor disk.

The rotor component basically only has the task of preventing the penetration of hot gas. There is usually no other function. Correspondingly, the mounting of the rotor component is kept simple in the usual way, with only one annular, axially extending shoulder engaging in a corresponding annular groove. To ensure the position of the rotor component between the two rotor disks, it is generally provided that the rotor component is supported on both sides of the respective rotor disk with a press fit. In this case, the rotor component is usually arranged at the location of the press fit on the side facing the rotor axis relative to the rotor disk. This is due in particular to the fact that, when centrifugal forces occur, the rotor component is subject to greater deformation than the rotor disks, which are solidly designed on the other hand.

Although the usual embodiment from the prior art has proven itself, depending on the design of the interference fit and the possible elastic deformations when the gas turbine is heated or when the gas turbine is cooled, different thermal expansions can occur in the rotor disks and the rotor component. Under certain circumstances, this can lead to the compressive stress in the press fit being lost. In contrast, the combination of the intended press fit with the deformations in the centrifugal forces due to a rotation of the rotor leads to possibly inadmissibly high compressive stresses.

The object of the present invention is therefore to ensure the position of the rotor component even during the heating and cooling of the gas turbine without exceeding the permissible stresses on the Ro gate component or on the rotor disks.

The object set is achieved by an embodiment according to the invention of a rotor according to the teaching of claim 1. Advantageous embodiments are the subject of the subclaims. A method for assembling the rotor is specified in claim 10.

The generic rotor is initially used for use in a gas turbine. Regardless of this, however, it is also possible to use the embodiment of the rotor in another To bring flow machine, for example in a steam turbine, to use.

At least the rotor has a first rotor disk and a second rotor disk that is directly and firmly connected to the first rotor disk. Here, the rotor disks each have a plurality of blade holding grooves which axially penetrate the respective rotor disk, distributed on the outer circumference. The blade retaining grooves serve to hold blades.

Furthermore, the first rotor disk has a circumferential first fastening projection extending axially towards the second rotor disk radially below the blade retaining grooves. Analogously, the second rotor disk has a circumferential second fastening projection extending axially towards the first rotor disk radially below the blade retaining grooves.

An annular rotor component is arranged between the two rotor disks in the area of the blade holding grooves and / or radially below the blade holding grooves. This encloses the rotor, which is located in sections within the rotor component, or sections of the two rotor disks. To center the rotor component relative to the rotor disks and at the same time for fastening, the rotor component has a circumferential, axially opening first annular groove at one axial end and a circumferential, axially opening second annular groove axially opposite.

The first fastening projection of the first rotor disk engages in the first annular groove and the second fastening projection of the second rotor disk engages in the second annular groove.

According to the invention, a defined position of the rotor component is now ensured without inadmissibly high stresses occurring by, when the rotor is at a standstill, when the rotor is essentially at room temperature, a Pressing is provided on the outer circumference of the first fastening projection. Correspondingly, a first groove outer flank of the first annular groove rests against a first protruding outer flank of the first fastening protrusion under pressure. In contrast, it is necessary that, at a standstill at room temperature, there is play radially opposite between a first inner flank of the first annular groove and a first inner flank of the first fastening projection (04).

The inventive arrangement of the interference fit when the rotor is at a standstill, in which the rotor is at room temperature overall, on the radially outer side with respect to the fastening projection on the first rotor disk, an inadmissible increase in the compressive stress is avoided in the centrifugal forces occurring.

It is particularly advantageous if the connection of the rotor component to the second rotor disk is essentially stress-free when the rotor is at a standstill at room temperature. For this, it is necessary that there is play between a second outer flank of the second annular groove and a second outer flank of the second fastening projection and that there is play between a second inner flank of the second annular groove and a second inner flank of the second fastening projection is.

An advantageous coordination with regard to the fastening of the rotor component between the rotor disks and the compressive stresses that occur, taking into account a rotation of the rotor when the gas turbine is started up with the associated expansions of the rotor component and the rotor disks, is particularly advantageous if in a first transition state at a first speed of the rotor , there is a change in the fastening state from the first rotor disk to the second rotor disk. The first speed is lower than the nominal speed at which the rotor is operated as intended. In this first one The transition state gives the first outer flank of the groove the same contact with the first outer flank of the protrusion, and the second inner flank of the groove also bears against the second inner flank of the protrusion. In contrast to this, there remains undiminished play between the first inside flank of the groove and the first inside protrusion flank, as well as play between the second outside flank of the groove (35) and the second outside flank of the protrusion.

In this case, the first speed is advantageously greater than 0.2 times the nominal speed. In contrast, the design should provide that the first speed is less than 0.6 times the nominal speed. To design the transition state, it can be assumed that both the rotor disks and the rotor component have approximately the same temperature, which corresponds approximately to room temperature or is above, but is clearly at a distance from the operating temperature.

By appropriately defining the diameter of the opposite fastening projections and the annular grooves, the position of the rotor component relative to the rotor disks can advantageously be guaranteed when the gas turbine is started up. With increasing speed and relatively greater expansion of the rotor component relative to the rotor disks, the pressure between the first outer flank of the protrusion and the outer flank of the groove decreases, with contact between the second inner flank of the groove and the second inner flank of the protrusion. In this respect, there is a change in the first transition state from the fixing of the rotor component on the first rotor disc to a fixing of the rotor component on the second rotor disc.

Furthermore, it is advantageous if, in a second transitional state, at a second rotational speed of the rotor, the rotor component is fixed by the second rotor disk. The second speed is higher than the first speed, but lower than the nominal speed of the Turbo machine. Correspondingly, there is a pressure between the second inner flank of the groove and the second inner flank of the projection. In contrast, there is play between the further contact surfaces, ie between the first outer flank of the groove and the first outer flank of the protrusion and between the inner flank of the first groove and the first inner flank of the protrusion and between the second outer flank of the groove and the second outer protrusion flank .

To design the second transitional state, a second speed can advantageously be assumed which corresponds to at least 0.8 times the nominal speed.

In the second transition state, the components have a second transition temperature. When the gas turbine is started up and all components are heated up, the rotor component usually heats up significantly faster than the more massive rotor disks due to its lower mass. Correspondingly, the second transition temperature is characterized in that the rotor component has almost reached the operating temperature, while the rotor disks, on the other hand, have a temperature that is significantly lower than the operating temperature, for example by approximately 30%.

Both for secure mounting of the rotor component between the two rotor disks and for supporting the rotor component on the rotor disks, it is particularly advantageous if there is support on both sides of the rotor component at the intended nominal speed. For this purpose, it is necessary that the first inner flank of the groove rests against the first inner flank of the protrusion under pressure and the second inner flank of the groove rests against the second inner flank of the protrusion under pressure. In contrast, there is a gap on the radially outer one, that is, a play between the first groove outer flank and the first protrusion outer flank and a play between the second groove outer flank and the second protrusion outer flank. So is Both the secure position of the rotor component and the load bearing of the centrifugal force are guaranteed on both sides.

An advantageous assembly of the rotor component in the rotor is made possible if the diameter of the first annular groove is set in a suitable ratio to the diameter of the first fastening projection. It is particularly advantageous here if the rotor component is heated to an assembly temperature of at least 100 ° C. and a maximum of 200 ° C. for assembly, while the rotor disks, on the other hand, are at room temperature. Taking into account the corresponding expansion of the rotor component due to the temperature increase, the required dimension of the first annular groove in relation to the first fastening projection can be determined. It is advantageous here if at the assembly temperature the pressure between the first groove outer flank and the first projection outer flank corresponds to a maximum of 10% of the pressure between the two components at room temperature. It is particularly advantageous here if the overlap existing at room temperature is essentially eliminated by means of the assembly temperature with a corresponding design of the diameter of the fastening projection and the annular groove.

If, at the assembly temperature, there should be a play between the first outer flank of the groove and the first outer flank of the protrusion, it should be noted, however, that there is no significant overlap on the radially inner side. Correspondingly, the pressure between the first groove inner flank and the first protrusion inner flank may in this case be a maximum of 10% of the pressure that is present at room temperature between the first groove outer flank and the first protrusion outer flank. It is advantageous in any case if a play remains between the first groove inner flank and the first projection inner flank even at the assembly temperature. In an advantageous embodiment of the rotor component, it has a cover section by means of which the blade holding grooves or the blade roots fastened in the blade holding grooves can be covered at least in sections by the rotor blade. For this it is necessary that the cover section extends in the circumferential direction and radially. The cover section is arranged radially outside of the first ring segment groove. It is further provided that the cover section rests axially with a support surface on an end face of the first rotor disk in the area between the blade holding grooves.

In a particularly advantageous manner, it can be provided that the rotor component has a cover section axially opposite on both sides.

At least it is furthermore advantageous if the support surface rests against the end surface under pressure when the cover section is elastically deformed. It can thus be ensured that when the turbo machine is in operation from standstill up to the nominal speed at operating temperature, the support surface is always in contact with the end face.

To achieve the advantageous compression between the support surface and the end face while avoiding increased assembly forces, it can advantageously be provided that the rotor component is heated to an assembly temperature between 100 ° C and 200 ° C, which is accompanied by a deformation of the rotor component and in particular of the cover section, so that in the intended position of the rotor component in the area of the annular groove relative to the fastening projection, the pressure between the support surface and the end face corresponds to a maximum of 10% of the pressure at room temperature. This state with the deformation in particular of the cover section in the axial direction in the area of the support surface is favored on the one hand by the design of the rotor component with the cover section arranged at the axial end. Furthermore, a design with a lower material thickness is effective in the central area between the two annular groove advantageous in terms of the desired deformation. On the other hand, the desired effect can be promoted by the targeted increase in temperature, preferably in the area of the first annular groove.

The corresponding design of the rotor component, in particular the definition of the diameter of the first annular groove and the second annular groove as well as the overlap between the support surface and the end face, taking into account the possible installation temperature of the rotor component, on the one hand, enables installation without too much effort and a secure location of the Rotor component guaranteed between the rotor disks in operation.

Furthermore, it is advantageous if, during the assembly of the rotor component on the first rotor disk, a free first expansion distance is maintained between a first projection end face of the first fastening projection and the first groove base of the first annular groove. The first expansion distance here is at least 0.5 mm. In contrast, it can be a disadvantage if the first expansion distance is more than 5 mm. A first expansion distance of at least 1 mm and a maximum of 2.5 mm is particularly advantageous.

Likewise, it can be provided that a second expansion distance is present between a second projection end face of the second fastening projection and the second groove base of the second annular groove. The second expansion distance should be a maximum of 0.2 times the first expansion distance.

The novel design of the rotor component with regard to its attachment between the two adjacent rotor disks leads to a new method for assembling the rotor.

The first rotor disk has to be made available once.

It is advantageous here if the first rotor disk is stored horizontally with the rotor axis aligned vertically.

In this case or in the following, the rotor component must be heated to an assembly temperature of at least 100 ° C.

A temperature of 200 ° C should not be exceeded here.

It is now a matter of attaching the rotor component to the first rotor disk. For this purpose, the rotor component is to be placed on the first rotor disk in such a way that the first annular groove is located above the first fastening projection. The rotor component can thus be pressed onto the first rotor disk until a support surface comes into contact with an end face of the rotor disk.

By pushing the rotor component further onto the first rotor disk with elastic deformation of the rotor component, the target position of the rotor component relative to the rotor disk is achieved, the target position being achieved by a previously defined first expansion distance between a first projection face of the first fastening projection and the first groove base of the first annular groove is defined.

The rotor component can now cool down, during which the rotor component must be held in position relative to the first rotor disk.

Finally, the second rotor disk can be placed or pressed onto the first rotor disk and the rotor component at the same time. The second fastening projection engages in the second annular groove.

In the following figures, an exemplary embodiment is outlined for a rotor according to the invention. Show it: 1 shows schematically in section the rotor component between two rotor disks;

Fig. 2 shows in detail the interference fit between the first loading fastening projection and the first annular groove;

Fig. 3 in detail the game between the second fastening supply projection and the second annular groove;

FIGS. 4-7 show the displacement of the rotor component relative to the rotor disks when the gas turbine is started up;

FIGS. 8-11 show the assembly of the rotor component on the first rotor disk.

In FIG. 1, the installation of the rotor component 21 between the rotor disks 01 and 11 is sketched schematically in a sectional illustration. The rotor disks 01, 11 each have blade holding grooves 02, 12 that penetrate axially through the respective rotor disk 01, 11 on the outer circumference. The blade retaining grooves 02, 12 are intended to accommodate blades. The respective rotor disks 01, 11 in turn each have a fastening projection 04, 14 running around the rotor axis 10. As can be seen, the fastening projections 04, 14 each extend axially to the opposite rotor disk. That located between the two rotor disks 01, 11

Rotor component 21 covers the space between the rotor disks 01, 11. For fastening, the rotor component 21 has an annular groove 24, 34 on each of the axially opposite sides, into which the respective fastening projection 04, 24 engages. The cover section 22, which 22 extends in the circumferential direction and radially, can also be seen at an axial end of the rotor component 21. This 22 covers the blade retaining grooves 02 in the first rotor disk. In Fig. 2, the press fit between tween the first fastening projection 04 and the first annular groove 24 is now outlined in detail. For this purpose, the rotor component 21 is shown axially offset for better visibility. The first rotor disk has a first outer projection flank 05 on the first fastening projection 04 on the radially outer side. The first projection inner flank 06 is located on the radially opposite side. The first projection end face 07 is located at the free end of the first fastening projection 04. Analogously to this, the rotor component 21 has a first groove on the first annular groove 24 on the radially outer side. Outer flank 25 and on the radially inner side a first groove inner flank 26. Opposite the first protrusion end face 07 is the first groove base 27 on the annular groove 24 available. This results from a geometric overlap 08 between the two corresponding components 01, 21. On the radially opposite inner side, however, there is a play 28 between the first projection inner flank and the first groove inner flank.

In FIG. 3, the assembly between the second rotor disk 11 and the rotor component 21 is sketched in detail, the rotor component 21 being offset analogously to FIG. 2. The second rotor disk 11 with rudimentary blade retaining groove 12 and the second fastening projection 14 can again be seen; this 14 has the second projection outer flank 15 on the radially outer side and the second projection inner flank 16 on the radially opposite side and the second projection end face 17 on the front side on. For this purpose, the second groove outer flank 35 and opposite the second groove inner flank 36 and opposite the second projection end face 17 the second groove base 27 are located on the second annular groove 34 on the radially outer side What can be seen here is that in the idle state or after assembly between the second fastening projection 14 and the second annular groove 34, there is play 09, 29 both on the radially outer side and on the radially inner side.

In the following sequence of figures 4 to 7, the state of the rotor component 21 in the assembly on the two fastening projections 04, 14 when starting the gas turbine with an increase in speed to the nominal speed wN and an increase in temperature to the operating temperature TN is outlined.

In FIG. 4, the state after assembly or in the idle state is sketched as described above. On the radially outer side of the first rotor disk 01, there is the interference fit due to the overlap 08, while, on the other hand, the play 28 is present on the radially inner side. There is also a free play 09, 29 on both sides of the second fastening projection 14.

FIG. 5 now shows the first transitional state when starting up the gas turbine. If the rotor is now set in motion, a first speed wΐ is reached, which wΐ is still well below the nominal speed wN, whereby the component temperatures T01, 11, 21 of the rotor disks 01, 14 and the rotor component can be slightly increased, but still far are removed from the operating temperature TN. It is essential that, in the first transitional state, the second groove inner flank 36 now rests against the second projection inner flank 16. Depending on the temperature T01, 11, 21 of the components 01, 11, 21 and the existing play 29 in the idle state, the installation takes place at different speeds, the play 29 preferably being set to a value that corresponds to an installation at approximately 0.3- times the nominal speed wN. As the speed increases and the temperature of the components increases, the pressure between the second fastening projection 14 and the rotor component 21 on the radially inner side increases, whereas the pressure between the first fastening projection 04 and the rotor component 21 on the radially outer side decreases. In the second transition state, which is sketched in FIG. 6, there is now a play on the radially outer side between the first fastening projection 04 and the rotor component 21 Free space is available. In this state, the second speed w2 lies between the first speed wΐ in the first transition state and the nominal speed wN, the second speed w2 being approximately 0.6 times the nominal speed wN. Due to the lower mass of the rotor component 21 relative to the rotor disks 01, 11, it heats up more quickly when the gas turbine is started up. Correspondingly, the component temperature T01, 11 of the rotor disks 01, 11 is significantly lower than that

Component temperature T21 of the rotor component, which T21 gradually approaches the operating temperature TN.

7 shows the state when the nominal speed wN and the operating temperature TN are reached. Starting from the second transitional state with an increase in the speed, the first inner protrusion flank 06 of the first fastening protrusion 04 rests on the first inner flank 26 of the first annular groove 24.

In the following FIGS. 8 to 11, the assembly of the rotor component 21 on the first rotor disk 01 is shown schematically. It should be noted at this point that, for advantageous assembly, the rotor disk 01 is aligned vertically and not horizontally as shown here, and the rotor component 21 is accordingly located above the rotor disk 0 1. As described above, it is provided that an overlap 08 between the first projection outer flank 0 5 of the first fastening projection 04 and the first groove outer flank 25 of the first annular groove 24 is present, so that a press fit is created. Furthermore, it is provided that the cover section 22 rests with a support surface 23 under pressure on an end surface 03 of the rotor disk 01. This requires the rotor component 21 to be heated for advantageous assembly.

8 shows the state of the rotor disk 01 and of the rotor component 21 located above it, the rotor component 21 having previously been heated to a temperature between 100.degree. C. and 200.degree. This achieves on the one hand that the diameter of the first groove outer flank 25 increases at least approximately to the diameter of the first projection outer flank 05, which enables the rotor component 21 to be pushed onto the first fastening projection 04 without excessive forces.

However, due to the special shape of the rotor component 21, a further effect is achieved when it is heated. This is the deformation of the rotor component 21 to the effect that the cover section 22 is deformed pointing away from the first rotor disk 01. Correspondingly, the distance between the end face 03 and the support surface 23 increases in contrast to the state at room temperature.

For this purpose, FIG. 9 sketches the position of the rotor component 21 on the rotor disk 01 after the rotor component 21 has taken place until the support surface 23 rests on the end face 03. In this case, an enlarged expansion distance 33 ′ remains between the first projection end face 07 and the first groove base 27.

The rotor component 21 is then pressed onto the first fastening projection 04 of the first rotor disk 01 until the previously defined expansion distance 33 is reached - see FIG. 10. The deformation continues the cover section 22, an initial pressure being produced between the support surface 23 and the end surface 03.

FIG. 11 now shows the state when, starting from the desired position, as shown in FIG. 10, the rotor component 21 cools down again. Care must be taken that the expansion distance 33 is kept constant. The temperature-related deformation of the cover section 22 now remains as a geometrically-related deformation with a pressure between the support surface 23 and the end face 03, here in FIG. 11 the theoretical state with an overlap 13 between the rotor component 21 and the rotor disk 01 is sketched.

01 first rotor disc

02 first shovel retaining groove

03 face

04 first fastening protrusion

05 first ledge on the outer flank

06 first projection inside flank

07 first protrusion face

08 overlap

09 game

10 rotor axis

11 second rotor disc

12 second blade retaining groove

13 Overlap

14 second fastening projection

15 second projection outer flank

16 second projection inner flank

17 second projection end face

21 Rotor component

22 cover section

23 support surface

24 first ring groove

25 first groove outer flank

26 first groove inside flank 27 first groove base

28 game

29 game

33 expansion distance 34 second ring groove

35 second groove outer flank

36 second groove inside flank

37 second groove base

Claims

1. Rotor, in particular of a gas turbine, with a first rotor disk (01) which (01) distributes a plurality of first blade retaining grooves (02) axially penetrating the rotor disk (01) on the outer circumference and one on the side facing the rotor axis below the first blade retaining grooves ( 02) arranged circumferential, axially extending first fastening projection (04), and with a second rotor disk (11) which (11) is firmly connected to the first rotor disk (01) and distributed on the outer circumference a plurality of axially penetrating rotor disk (11) second blade holding grooves (12) and a circumferential, axially extending second fastening projection (14) arranged on the side facing the rotor axis below the second bucket holding grooves (12), and with an annular circumferential rotor component (21) which (21) has a circumferential, axially opening first annular groove (24) and on the opposite side a circumferential axially opening second annular groove (34), wherein the first fastening projection (04) engages in the first annular groove (24) and the second fastening projection (14) engages in the second annular groove (34), characterized in that at a standstill

- A first groove outer flank (25) of the first annular groove (24) rests against a first protrusion outer flank (05) of the first fastening protrusion (04) under pressure and

- There is play between a first inner flank (26) of the first annular groove (24) and a first inner flank (06) of the first fastening projection (04).

2. Rotor according to claim 1, characterized in that it continues at a standstill

- Between a second groove outer flank (35) of the second annular groove (34) and a second projection outer flank (15) of the second fastening projection (14) is a game and

- There is play between a second inner groove flank (36) of the second annular groove (34) and a second inner protrusion flank (16) of the second fastening protrusion (14).

3. Rotor according to claim 2, characterized in that in a first transition state at a first speed lower than the intended nominal speed, in particular at a first speed between 0.2 times and 0.6 times the nominal speed,

- The first groove outer flank (25) rests against the first projection outer flank (05) and

- There is a game between the first groove inner flank (26) and the first projection inner flank (06) and

- There is a game between the second groove outer flank (35) and the second projection outer flank (15) and

- The second groove inner flank (36) rests against the second projection inner flank (16).

4. Rotor according to claim 3, characterized in that in a second transitional state at a second speed greater than the first speed and lower than the intended nominal speed, in particular with a second speed of at least 0.8 times the nominal speed,

- There is a game between the first groove outer flank (25) and the first projection outer flank (05) and

- The second groove inner flank (36) rests on the second projection inner flank (16) under pressure.

5. Rotor according to one of claims 1 or 4, characterized in that that at the intended nominal speed

- The first groove inner flank (26) rests on the first projection inner flank (06) under pressure and

- The second groove inner flank (36) rests against the second projection inner flank (16) under pressure.

6. Rotor according to one of claims 1 or 5, characterized in that at an assembly temperature of the rotor component (21) of at least 100 ° C and a maximum of 200 ° C

- the pressure between the first groove outer flank (25) and the first projection outer flank (05) corresponds to a maximum of 10% of the pressure at room temperature and

- the pressure between the first groove inner flank (26) and the first protrusion inner flank (06)) corresponds to a maximum of 10% of the pressure between the first groove outer flank (25) and the first protrusion outer flank (05) at room temperature, in particular there is a play between the first groove inner flank (26) and the first projection inner flank (06).

7. Rotor according to one of claims 1 to 6, characterized in that the rotor component (21) has a circumferentially and radially extending cover section (22) which (22) at least partially covers the first blade retaining grooves (02) and with a support surface (23) rests against an end face (03) of the first rotor disk in the area between the blade holding grooves (02).

8. Rotor according to claim 7, characterized in that that the support surface (23) rests against the end face (03) under pressure when the cover section (22) is elastically deformed.

9. Rotor according to claim 8, characterized in that at an assembly temperature of the rotor component (21) of at least 100 ° C and a maximum of 200 ° C, the pressure of the support surface (23) on the end face (03) corresponds to a maximum of 10% of the pressure at room temperature .

10. Rotor according to one of claims 1 to 9, characterized in that after the assembly of the rotor at least before the rotor is heated between a first projection end face (07) of the first fastening projection (04) and the first groove base (27) of the first Annular groove (24) there is a free first expansion distance, the first expansion distance being at least 0.5 mm and at most 5 mm, in particular at least 1 mm and at most 2.5 mm.

11. Rotor according to claim 10, characterized in that between a second projection end face (17) of the second fastening projection (14) and the second groove base (37) of the second annular groove (34) there is a free second expansion distance or an abutment, wherein the second expansion distance corresponds to a maximum of 0.2 times the first expansion distance.

12. A method for assembling a rotor according to one of the preceding claims with

- Provision of the first rotor disk (01);

- Heating the rotor component (21) to an assembly temperature of at least 100 ° C and a maximum of 200 ° C;

- Placing and / or pressing the rotor component (21) onto the first rotor disk (01) with the support surface (23) in contact with the end surface (03); - The rotor component (21) is pushed further onto the first rotor disk (01) until a predefined expansion distance is reached between a first projection end face (07) of the first fastening projection (04) and the first groove base (27) of the first annular groove (24);

- Cooling of the rotor component (21) while holding the first rotor disk (01) and the rotor component (21) together;

- Placing and / or pressing the second rotor disk (11) onto the first rotor disk (01) and the rotor component (21) at the same time.