EP4013950B1 - Rotor comprising a rotor component arranged between two rotor discs - Google Patents

Description

The invention relates to a rotor of a gas turbine, which has at least two interconnected rotor disks, between which an annular rotor component is arranged. The invention also relates to a method for assembling a rotor. Such rotor arrangements are, for example, from DE102014115197A1 or from the EP2639409A2 known.

Various designs of rotors for use in gas turbines with interconnected rotor disks are known from the prior art, with an annular rotor component being arranged between the rotor disks to shield the inner region of the rotor from the hot gas flowing through the gas turbine. The two rotor disks each have a plurality of rotor blades distributed around the outer circumference. Between the two rows of blades there is a row of guide blades distributed around the circumference, each of which is attached to the stationary housing. Due to 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, in some gas turbines an annular rotor component is arranged between the two adjacent rotor disks. 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 ingress of hot gas. There is usually no other function available. Accordingly, the storage of the rotor component is kept simple in the usual way, with only an 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 mounted on both sides of the respective rotor disk with a press fit. The rotor component is usually arranged at the point of press fit on the side facing the rotor axis relative to the rotor disk. This is due in particular to the fact that the rotor component is subject to greater deformation when centrifugal forces occur than the solid rotor disks.

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

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

The object is achieved by an embodiment of a rotor according to the invention 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 in a gas turbine. Regardless of this, however, it is also possible to use a different embodiment of the rotor Turbomachine, for example in a steam turbine, to be used.

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 distributed on the outer circumference and axially penetrating the respective rotor disk. The blade holding grooves are used to hold rotor blades.

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

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. For centering 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, axially opposite, a circumferential, axially opening second annular groove. 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 impermissibly high voltages occurring, in that when the rotor is at a standstill, in which the rotor is essentially at room temperature, Pressing is provided on the outer circumference of the first fastening projection. Correspondingly, a first groove outer flank of the first annular groove rests under pressure on a first projection outer flank of the first fastening projection. In contrast, it is necessary that, when stationary at room temperature, there is play radially opposite between a first groove inner flank of the first annular groove and a first projection inner flank of the first fastening projection (04).

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

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 purpose, it is necessary that there is a game between a second groove outer flank of the second annular groove and a second projection outer flank of the second fastening projection and that there is a game between a second groove inner flank of the second annular groove and a second projection 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 starting up the gas turbine 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 , a change in the fastening state from the first rotor disk to the second rotor disk takes place. The first speed is lower than the nominal speed at which the rotor is operated as intended. In this first one Transition state continues to ensure that the first groove outer flank rests on the first projection outer flank, with the second groove inner flank also resting on the second projection inner flank. In contrast, there remains undiminished play between the first groove inner flank and the first projection inner flank as well as play between the second groove outer flank (35) and the second projection outer flank.

Here, 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 approximately corresponds to or is above room temperature, but is significantly away from the operating temperature.

By appropriately determining the diameters of the opposing fastening projections and the annular grooves, the position of the rotor component relative to the rotor disks when starting up the gas turbine can advantageously be ensured. With increasing speed and relatively greater expansion of the rotor component relative to the rotor disks, the pressure between the first projection outer flank and the first groove outer flank decreases, with contact being created between the second groove inner flank and the second projection inner flank. In this respect, there is a change in the first transition state from fixing the rotor component to the first rotor disk to fixing the rotor component to the second rotor disk.

Furthermore, it is advantageous if, in a second transition state at a second speed of the rotor, the fixation of the rotor component is taken over by the second rotor disk. The second speed is higher than the first speed, but lower than the nominal speed Fluid machine. Accordingly, there is a pressure between the second groove inner flank and the second projection inner flank. In contrast, there is play between the further contact surfaces, ie between the first groove outer flank and the first projection outer flank as well as between the first groove inner flank and the first projection inner flank and between the second groove outer flank and the second projection outer flank .

To design the second transition 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 start to heat up, the rotor component usually heats up significantly faster than the more massive rotor disks due to its lower mass. Accordingly, the second transition temperature is characterized in that the rotor component has approximately reached the operating temperature, while the rotor disks, on the other hand, have a significantly lower temperature than the operating temperature, for example by approximately 30%.

Both for secure storage 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 groove inner flank rests under pressure on the first projection inner flank and the second groove inner flank under pressure rests on the second projection inner flank. In contrast, there is a gap on the radially outer side, that is, a play between the first groove outer flank and the first projection outer flank and a play between the second groove outer flank and the second projection outer flank. Thus is Both the safe 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 if the rotor component is heated for assembly to an assembly temperature of at least 100 ° C and a maximum of 200 ° C, while the rotor disks 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 can be determined in relation to the first fastening projection. 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 that exists at room temperature is essentially eliminated by means of the assembly temperature with appropriate design of the diameter of the fastening projection and annular groove.

If there is a play between the first groove outer flank and the first projection outer flank at the assembly temperature, it should be noted that there is no significant overlap on the radially inner side. Accordingly, the pressure between the first groove inner flank and the first projection inner flank in this case may be a maximum of 10% of the pressure that exists at room temperature between the first groove outer flank and the first projection outer flank. In any case, it is advantageous if there remains a play between the first groove inner flank and the first projection inner flank, even at the assembly temperature.

In an advantageous design of the rotor component, it has a cover section by means of which the blade holding grooves or the blade feet of rotor blades fastened in the blade holding grooves can be covered at least in sections. For this it is necessary that the cover section extends in the circumferential direction and radially. The cover section is arranged radially outside the first ring segment groove. It is further provided that the cover section with a support surface rests axially 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 on both sides, axially opposite.

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

In order to achieve the advantageous pressure 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 when 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 condition 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 in the middle area has an effect between the two annular groove is 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 appropriate design of the rotor component, in particular the determination 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 assembly temperature of the rotor component, on the one hand enables assembly without too much effort as well as a secure position of the rotor component between the rotor disks during operation.

Furthermore, it is advantageous if, when mounting 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 is at least 0.5 mm. In contrast, it can be disadvantageous 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 correspond to 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 must be provided once. It is advantageous here if the first rotor disk is stored horizontally with the rotor axis aligned vertically.

The rotor component must be heated to an assembly temperature of at least 100 °C. A temperature of 200 °C should not be exceeded.

Now it is time to attach the rotor component to the first rotor disk. For this purpose, the rotor component must 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 further pushing the rotor component onto the first rotor disk with an elastic deformation of the rotor component, the desired position of the rotor component relative to the rotor disk is achieved, the desired position being determined by a predefined first expansion distance between a first projection end 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 time the rotor component must be kept 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.

Fig. 1

schematisch im Schnitt das Rotorbauteil zwischen zwei Rotorscheiben;

Fig. 2

im Detail die Presspassung zwischen dem ersten Befestigungsvorsprung und der ersten Ringnut;

Fig. 3

im Detail das Spiel zwischen dem zweiten Befestigungsvorsprung und der zweiten Ringnut;

Figuren 4-7

die Verschiebung des Rotorbauteils relativ zu den Rotorscheiben beim Hochfahren der Gasturbine;

Figuren 8-11

die Montage des Rotorbauteils an der ersten Rotorscheibe.

An exemplary embodiment of a rotor according to the invention is sketched in the following figures. Show it:

Fig. 1

schematically in section the rotor component between two rotor disks;

Fig. 2

in detail, the press fit between the first fastening projection and the first annular groove;

Fig. 3

in detail the play between the second fastening projection and the second annular groove;

Figures 4-7

the displacement of the rotor component relative to the rotor disks when starting up the gas turbine;

Figures 8-11

the assembly of the rotor component on the first rotor disk.

In the Fig. 1 the installation of the rotor component 21 between the rotor disks 01 and 11 is sketched schematically in a sectional view. The rotor disks 01, 11 each have axially penetrating blade holding grooves 02, 12 distributed on the outer circumference of the respective rotor disk 01, 11. The blade holding grooves 02, 12 are intended to hold rotor 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. The rotor component 21 located between the two rotor disks 01, 11 covers the space between the rotor disks 01, 11. For fastening, the rotor component 21 has an annular groove 24, 34 on the axially opposite sides, into which the respective fastening projection 04, 24 engages. Furthermore, the cover section 22 can be seen at an axial end of the rotor component 21, which 22 extends in the circumferential direction and radially. This 22 covers the blade holding grooves 02 in the first rotor disk.

In the Fig. 2 The press fit between the first fastening projection 04 and the first annular groove 24 will now be outlined in detail. For better visibility, the rotor component 21 is shown axially offset. The first rotor disk has a first projection outer 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 projection end face 07, the first groove base 27 is located on the annular groove 24. When the rotor is at rest at room temperature, or after assembly of the rotor, there is a press fit between the first projection outer flank 05 and the first groove outer flank 25 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 the Fig. 3 The assembly between the second rotor disk 11 and the rotor component 21 is outlined in detail, analogous to Fig. 2 the rotor component 21 is shown offset. The second rotor disk 11 can again be seen with the blade holding groove 12 and the second fastening projection 14. 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 . For this purpose, the second groove outer flank 35 is located on the rotor component 21 on the second annular groove 34 on the radially outer side, as well as the second groove inner flank 36 opposite and the second groove base 27 opposite the second projection end face 17. Zu It can be seen that in the resting state or after assembly between the second fastening projection 14 and the second annular groove 34 there is a 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 assembly on the two fastening projections 04, 14 when starting up the gas turbine with an increase in the speed to the nominal speed ωN and an increase in the temperature to the operating temperature TN is outlined.

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

The Fig. 5 now shows the first transition state when starting up the gas turbine. If the rotor is now set in motion, a first speed ω1 is reached, which ω1 is still significantly below the nominal speed ωN, whereby the component temperatures T01, 11, 21 of the rotor disks 01, 14 and of the rotor component can be slightly increased, but still far from the operating temperature TN. It is important that in the first transition state the second groove inner flank 36 now comes into contact with 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 system takes place at different speeds, with the game 29 preferably being set to a value that results in a system at approximately 0.3 - times the nominal speed ωN.

As the speed increases and the temperatures of the components increase, 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 in Fig. 6 is outlined, there is now a play on the radially outer side between the first fastening projection 04 and the rotor component 21. This means that there is a free space between the first projection outer flank 05 and the first groove outer flank 25. In this state, the second speed ω2 is between the first speed ω1 in the first transition state and the nominal speed ωN, whereby the second speed ω2 can correspond to approximately 0.6 times the nominal speed ωN. 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. Accordingly, the component temperature T01, 11 of the rotor disks 01, 11 is significantly lower than the component temperature T21 of the rotor component, which T21 gradually approaches the operating temperature TN.

Fig. 7 shows the state when the nominal speed ωN and the operating temperature TN have been reached. Starting from the second transition state with an increase in the speed, the first inner projection flank 06 of the first fastening projection 04 comes into contact with the first groove inner flank 26 of the first annular groove 24.

In the following Figures 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 accordingly the rotor component 21 is located above the rotor disk 01. As described above, it is provided that there is 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 with a support surface 23 rests under pressure on an end face 03 of the rotor disk 01. This requires the rotor component 21 to be heated up for advantageous assembly.

The shows this Fig. 8 the condition of the rotor disk 01 and the rotor component 21 located above it, the rotor component 21 having previously been heated to a temperature between 100 ° C and 200 ° C. On the one hand, this ensures 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, the special shape of the rotor component 21 achieves a further effect when heated. This is the deformation of the rotor component 21 in such a way that the cover section 22 is deformed in a direction away from the first rotor disk 01. The distance between the end face 03 and the support surface 23 increases accordingly in contrast to the condition at room temperature.

The outlines this Fig. 9 the position of the rotor component 21 on the rotor disk 01 after the rotor component 21 has come into contact with the support surface 23 on the end face 03. An increased expansion distance 33' remains between the first projection end face 07 and the first groove base 27.

Subsequently, the rotor component 21 is pressed further onto the first fastening projection 04 of the first rotor disk 01 until the previously defined expansion distance 33 is reached - see Fig. 10 . It continues to deform the cover section 22, whereby an initial pressure is created between the support surface 23 and the end face 03.

01

erste Rotorscheibe

02

erste Schaufelhaltenut

03

Stirnfläche

04

erster Befestigungsvorsprung

05

erste Vorsprung-Außenflanke

06

erste Vorsprung-Innenflanke

07

erste Vorsprung-Stirnfläche

08

Überschneidung

09

Spiel

10

Rotorachse

11

zweite Rotorscheibe

12

zweite Schaufelhaltenut

13

Überschneidung

14

zweiter Befestigungsvorsprung

15

zweite Vorsprung-Außenflanke

16

zweite Vorsprung-Innenflanke

17

zweite Vorsprung-Stirnfläche

21

Rotorbauteil

22

Abdeckabschnitt

23

Stützfläche

24

erste Ringnut

25

erste Nut-Außenflanke

26

erste Nut-Innenflanke

27

erster Nutgrund

28

Spiel

29

Spiel

33

Dehnungsabstand

34

zweite Ringnut

35

zweite Nut-Außenflanke

36

zweite Nut-Innenflanke

37

zweiter Nutgrund

In the Fig. 11 The state is now shown if, starting from the target position, as in Fig. 10 shown, the rotor component 21 cools down again. It is important to ensure that the expansion distance 33 is kept constant. The temperature-related deformation of the cover section 22 now remains as a geometrically caused deformation with a pressure between the support surface 23 and the end face 03. In Fig. 11 the theoretical state is outlined with an overlap 13 between the rotor component 21 and the rotor disk 01.

01

first rotor disk

02

first blade holding groove

03

face

04

first fastening projection

05

first projection outside flank

06

first lead inside flank

07

first projection end face

08

overlap

09

Game

10

Rotor axis

11

second rotor disk

12

second blade holding 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 inner flank

27

first groove base

28

Game

29

Game

33

Stretch distance

34

second ring groove

35

second groove outer flank

36

second groove inner flank

37

second groove base

Claims (12)

1. Rotor of a gas turbine,

   having a first rotor disk (01) which (01) has, distributed on the outer circumference, a plurality of first blade retention grooves (02) penetrating the rotor disk (01) axially and has an encircling, axially extending first fastening projection (04) arranged, on the side pointing toward the rotor axis, below the first blade retention grooves (02), and

   having a second rotor disk (11) which (11) is fixedly connected to the first rotor disk (01) and has, distributed on the outer circumference, a plurality of second blade retention grooves (12) penetrating the rotor disk (11) axially and has an encircling, axially extending second fastening projection (14) arranged, on the side pointing toward the rotor axis, below the second blade retention grooves (12), and

   having a ring-shaped encircling rotor component (21) which (21) has, on one side, an encircling, axially opening first annular groove (24) and, on the opposite side, an encircling, axially opening second annular groove (34), wherein the first fastening projection (04) engages into the first annular groove (24) and the second fastening projection (14) engages into the second annular groove (34),

   characterized

   in that, in a standstill state,

   - a first groove outer flank (25) of the first annular groove (24) bears under contact pressure against a first projection outer flank (05) of the first fastening projection (04), and

   - a clearance is present between a first groove inner flank (26) of the first annular groove (24) and a first projection inner flank (06) of the first fastening projection (04).
2. Rotor according to Claim 1,
   characterized
   in that, in a standstill state, furthermore,

   - a clearance is present 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), and

   - a clearance is present between a second groove inner flank (36) of the second annular groove (34) and a second projection inner flank (16) of the second fastening projection (14).
3. Rotor according to Claim 2,
   characterized
   in that, in a first transition state in the presence of a first rotational speed lower than the intended nominal rotational speed, in particular with a first rotational speed between 0.2 times and 0.6 times the nominal rotational speed,

   - the first groove outer flank (25) bears against the first projection outer flank (05), and

   - a clearance is present between the first groove inner flank (26) and the first projection inner flank (06), and

   - a clearance is present between the second groove outer flank (35) and the second projection outer flank (15), and

   - the second groove inner flank (36) bears against the second projection inner flank (16).
4. Rotor according to Claim 3,
   characterized
   in that, in a second transition state in the presence of a second rotational speed higher than the first rotational speed and lower than the intended nominal rotational speed, in particular with a second rotational speed of at least 0.8 times the nominal rotational speed,

   - a clearance is present between the first groove outer flank (25) and the first projection outer flank (05), and

   - a clearance is present between the first groove inner flank (26) and the first projection inner flank (06), and

   - a clearance is present between the second groove outer flank (35) and the second projection outer flank (15), and

   - the second groove inner flank (36) bears under contact pressure against the second projection inner flank (16).
5. Rotor according to either of Claims 1 and 4,
   characterized
   in that, in the presence of the intended nominal rotational speed,

   - a clearance is present between the first groove outer flank (25) and the first projection outer flank (05), and

   - the first groove inner flank (26) bears under contact pressure against the first projection inner flank (06), and

   - a clearance is present between the second groove outer flank (35) and the second projection outer flank (15), and

   - the second groove inner flank (36) bears under contact pressure against the second projection inner flank (16).
6. Rotor according to either of Claims 1 and 5,
   characterized
   in that, in the presence of an installation temperature of the rotor component (21) of at least 100°C and at most 200°C,

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

   - the contact pressure between the first groove inner flank (26) and the first projection inner flank (06) corresponds to at most 10% of the contact pressure between the first groove outer flank (25) and the first projection outer flank (05) at room temperature, and, in particular, a clearance is present between the first groove inner flank (26) and the first projection inner flank (06).
7. Rotor according to any of Claims 1 to 6,
   characterized
   in that the rotor component (21) has a covering portion (22) extending in a circumferential direction and radially, which (22) covers the first blade retention grooves (02) at least in sections and bears with a support surface (23) against an end surface (03) of the first rotor disk in the region between the blade retention grooves (02).
8. Rotor according to Claim 7,
   characterized
   in that the support surface (23) bears under contact pressure, with elastic deformation of the covering portion (22), against the end surface (03).
9. Rotor according to Claim 8,
   characterized
   in that, in the presence of an installation temperature of the rotor component (21) of at least 100°C and at most 200°C, the contact pressure of the support surface (23) against the end surface (03) corresponds to at most 10% of the contact pressure at room temperature.
10. Rotor according to any of Claims 1 to 9,
    characterized
    in that, after the installation of the rotor, at least prior to a heating-up of the rotor, a free first expansion spacing is present between a first projection end surface (07) of the first fastening projection (04) and the first groove base (27) of the first annular groove (24), wherein the first expansion spacing amounts to 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 a free second expansion spacing or contact is present between a second projection end surface (17) of the second fastening projection (14) and the second groove base (37) of the second annular groove (34), wherein the second expansion spacing corresponds to at most 0.2 times the first expansion spacing.
12. Method for installing a rotor according to any of the preceding claims, comprising:

    - providing the first rotor disk (01);

    - heating up the rotor component (21) to an installation temperature of at least 100°C and at most 200°C;

    - placing and/or pressing the rotor component (21) onto the first rotor disk (01) with contact of the support surface (23) against the end surface (03);

    - pushing the rotor component (21) further onto the first rotor disk (01) until a predefined expansion spacing between a first projection end surface (07) of the first fastening projection (04) and the first groove base (27) of the first annular groove (24) is attained;

    - cooling the rotor component (21) and, in the process, holding the first rotor disk (01) and the rotor component (21) together;

    - placing and/or pressing the second rotor disk (11) onto simultaneously the first rotor disk (01) and the rotor component (21).

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