CN114599859B - Rotor with rotor components arranged between two rotor disks - Google Patents
Rotor with rotor components arranged between two rotor disks Download PDFInfo
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- CN114599859B CN114599859B CN202080073026.2A CN202080073026A CN114599859B CN 114599859 B CN114599859 B CN 114599859B CN 202080073026 A CN202080073026 A CN 202080073026A CN 114599859 B CN114599859 B CN 114599859B
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- rotor
- groove
- projection
- outer side
- gap
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- 230000006835 compression Effects 0.000 claims abstract description 11
- 238000007906 compression Methods 0.000 claims abstract description 11
- 238000009434 installation Methods 0.000 claims description 12
- 230000007704 transition Effects 0.000 claims description 9
- 238000010438 heat treatment Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 5
- 230000005489 elastic deformation Effects 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 19
- 230000000694 effects Effects 0.000 description 4
- 230000007423 decrease Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/37—Retaining components in desired mutual position by a press fit connection
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a rotor of a gas turbine, comprising two adjacent rotor disks (01, 11) on which rotor blades are fastened in each case, wherein an annular rotor component (21) is arranged between the rotor disks (01, 11), said rotor component having circumferential annular grooves (24, 34) at opposite ends, into which circumferential fastening projections (04, 14) of the respective rotor disk (01, 11) engage in each case. It is proposed that, in the rest state of the rotor, the first groove outer side (25) of the first annular groove (24) bears under compression against the first projection outer side (05) of the first fastening projection (04), and that a gap is present between the first groove inner side (26) of the first annular groove (24) and the first projection inner side (06) of the first fastening projection (04).
Description
Technical Field
The invention relates to a rotor of a gas turbine, comprising at least two interconnected rotor disks, between which an annular rotor component is arranged.
Background
Different embodiments of rotors with interconnected rotor disks for use in gas turbines are known in the prior art, wherein annular rotor components are arranged between the rotor disks for shielding the interior region of the rotor from the hot gas flowing through the gas turbine. In this case, the two rotor disks have a plurality of rotor blades distributed over the outer circumference. Between the two rows of rotor blades there is a row of guide blades arranged circumferentially, which are each fastened to a stationary housing. In this case, due to the rotation of the rotor, a gap must exist between the guide vane and the rotor vane. The gap can in principle allow the hot gas to enter radially into the region inside the guide vane. In order to keep the hot gases away from the rotor interior, in some gas turbines an annular rotor member is provided between two adjacent rotor disks. For this purpose, the rotor component is supported on both sides of the rotor disk.
The rotor component is based solely on the purpose of being able to prevent the ingress of hot gases. Another function is typically not present. Accordingly, the support of the rotor component is usually kept simple, wherein only one annular, axially extending shoulder engages into the respective annular groove.
In order to ensure the position of the rotor component between the two rotor disks, it is generally proposed that: the rotor components are supported on both sides of the respective rotor disk by means of a press fit. In this case, the rotor component is usually arranged on the side facing the rotor axis relative to the rotor disk at the point of the press fit. This is due in particular to the fact that the rotor component undergoes a greater deformation when centrifugal forces occur than in the case of a rotor disk which is constructed in comparison with this.
Although the common embodiments in the prior art have proven successful, different thermal expansions can occur at the rotor disk and at the rotor component, depending on the design of the press fit and the possible elastic deformation during heating or cooling of the gas turbine. In some cases, this may cause: compressive stress loss in the press fit. In contrast, the combination of the provided press fit and the deformation caused by the centrifugal force due to the rotation of the rotor may cause unacceptably high compressive stresses.
Disclosure of Invention
It is therefore an object of the invention to ensure the position of the rotor component even when the gas turbine is being heated and cooled, without exceeding the permissible stresses on the rotor component or rotor disk.
The proposed object is achieved by an embodiment of a rotor according to the invention, which has: a first rotor disk, which has a plurality of first blade holding grooves and a circumferential, axially extending first fastening projection, which extends axially through the first rotor disk, which is arranged below the first blade holding grooves on the side facing the rotor axis, and a second rotor disk, which is firmly connected to the first rotor disk, which has a plurality of second blade holding grooves and a circumferential, axially extending second fastening projection, which extends axially through the second rotor disk, which is arranged below the second blade holding grooves on the side facing the rotor axis, and which has a circumferential, axially open first annular groove on the opposite side, and which engages into the first rotor disk, and which has a circumferential, axially open second annular groove on the side facing the rotor axis, which engages into the first annular groove, and which presses against the first annular groove on the outside in the first annular groove, and which presses against the first flange on the outside in the first annular groove, and the first flange on the first annular groove, and the second flange being in the state of compression against the first flange. Advantageous embodiments are the following subject matter. A method of installing a rotor is given below.
Rotors of this type were originally used in gas turbines. However, independently of this, it is also possible to use a rotor embodiment in another fluid machine, for example in a steam turbine.
The rotor has at least a first rotor disk and a second rotor disk directly and firmly connected to the first rotor disk. In this case, the rotor disks each have a plurality of blade holding grooves, which extend axially through the respective rotor disk, in a manner distributed over the outer circumference. In this case, the blade holding slot is used to accommodate the rotor blade.
Furthermore, the first rotor disk has a circumferential first fastening projection radially below the blade holding groove, which extends in the axial direction toward the second rotor disk. Similarly, the second rotor disk has a circumferential second fixing projection radially below the blade holding groove, which extends in the axial direction toward the first rotor disk.
An annular rotor component is arranged in the region of the blade holding groove and/or between the two rotor disks radially below the blade holding groove. The annular rotor member encloses sections of the rotor or of two rotor disks with sections located inside the rotor member. For centering the rotor component relative to the rotor disk and for fixing at the same time, the rotor component has a circumferential, axially open first annular groove at the axial end and a circumferential, axially open second annular groove axially opposite. Here, the first fixing projection of the first rotor disk engages into the first annular groove, and the second fixing projection of the second rotor disk engages into the second annular groove.
According to the invention, a defined position of the rotor component is now ensured without the occurrence of unacceptably high stresses, in that: in a stationary state of the rotor having substantially room temperature, pressing is provided on the outer circumference of the first fixing projection. Correspondingly, the first groove outer side of the first annular groove is pressed against the first projection outer side of the first fixing projection. Contrary to the requirements: when at rest at room temperature, a gap is present between the first groove inner side of the first annular groove and the first projection inner side of the first fixing projection (04) in a diametrically opposed manner.
By the arrangement according to the invention of the press fit when the rotor is in a stationary state with room temperature on the whole of the rotor, on the radially outer side of the first rotor disk with respect to the fixing projections, an impermissible increase in the compressive stress when centrifugal forces occur is avoided.
It is particularly advantageous here if the connection of the rotor component to the second rotor disk is substantially stress-free when the rotor is stationary at room temperature. For this purpose, it is necessary that a gap is present between the second groove outer side of the second annular groove and the second projection outer side of the second fastening projection, and a gap is present between the second groove inner side of the second annular groove and the second projection inner side of the second fastening projection.
With regard to an advantageous coordination of the fixing of the rotor components between the rotor disks and the compressive stresses occurring in consideration of the rotation of the rotor at the start-up of the gas turbine and the accompanying expansion of the rotor components and the rotor disks, it is particularly advantageous if the fixing state from the first rotor disk to the second rotor disk changes in a first transitional state of the rotor at a first rotational speed. In this case, the first rotational speed is lower than the rated rotational speed of the rotor according to the prescribed operation. In this first transitional state, the contact of the first groove outer side on the first projection outer side is not reduced, wherein the second groove inner side also contacts the second projection inner side. In contrast, the gap between the first groove inner side surface and the first projection inner side surface and the gap between the second groove outer side surface (35) and the second projection outer side surface remain unchanged.
In this case, the first rotational speed is advantageously greater than 0.2 times the nominal rotational speed. In contrast, the design should provide that the first rotational speed is less than 0.6 times the nominal rotational speed. For the design of the transition state it can be assumed that the rotor disk and the rotor component have approximately the same temperature, which approximately corresponds to or is higher than room temperature, however differs significantly from the operating temperature.
By correspondingly determining the diameters of the opposing fastening projections and of the annular groove, the position of the rotor component relative to the rotor disk at the start-up of the gas turbine can advantageously be ensured. As the rotational speed of the rotor member relative to the rotor disk increases and expands relatively more, the compressive force between the first lobe outer side and the first slot outer side decreases, wherein contact is made between the second slot inner side and the second lobe inner side. In this connection, the first transition state changes from the fastening of the rotor component to the first rotor disk to the fastening of the rotor component to the second rotor disk.
In a second transitional state, the rotor component is advantageously fastened to the second rotor disk at a second rotational speed of the rotor. In this case, the second rotational speed is higher than the first rotational speed, but lower than the nominal rotational speed of the gas turbine. Accordingly, there is compression between the second groove inner side and the second protrusion inner side. In contrast, gaps exist between the further contact surfaces, i.e. between the first groove outer side and the first projection outer side and between the first groove inner side and the first projection inner side and between the second groove outer side and the second projection outer side.
In order to design the second transition state, it can be advantageously provided that the second rotational speed corresponds to at least 0.8 times the nominal rotational speed.
In the second transition state, the component has a second transition temperature. When the gas turbine is started and all components are heated, the particularly low mass of the rotor components generally heats up significantly faster than the more solid rotor disks. Accordingly, the second transition temperature is characterized in that the rotor component approximately reaches the operating temperature, while the rotor disk has a temperature that is significantly lower than the operating temperature, for example, a temperature that is about 30% lower.
It is particularly advantageous if the rotor component is supported on both sides at a defined nominal rotational speed, if the rotor component is firmly supported between two rotor disks and if the rotor component is supported on the rotor disks. For this purpose, the first groove inner side is pressed against the first projection inner side, while the second groove inner side is pressed against the second projection inner side. In contrast, there is a gap on the radially outer side, that is, a gap between the first groove outer side face and the first projection outer side face and a gap between the second groove outer side face and the second projection outer side face. Thus, a safe position of the rotor component and load absorption of centrifugal forces are ensured on both sides.
If the diameter of the first annular groove is determined in a suitable ratio to the diameter of the first fixing projection, an advantageous installation of the rotor component in the rotor can be achieved. In this case, it is particularly advantageous for the installation to heat the rotor component to an installation temperature of at least 100 ℃ and at most 200 ℃, whereas the rotor disk has room temperature in contrast. The required dimensions of the first annular groove relative to the first fastening projection can be determined taking into account the corresponding expansion of the rotor component due to the temperature increase. In this case, it is advantageous if, at the mounting temperature, the pressing force between the first groove outer side and the first projection outer side corresponds to a maximum of 10% of the pressing force between the two components at room temperature. In this case, it is particularly advantageous if the diameters of the fastening projections and the annular grooves are designed accordingly, with the aid of the installation temperature, to substantially eliminate the overlap that exists at room temperature.
If a gap is created between the first groove outer side and the first projection outer side at the mounting temperature, it is to be noted in contrast that, however, no significant overlap occurs on the radially inner side. Accordingly, the pressing force between the first groove inner side face and the first projection inner side face can in this case be a maximum of 10% of the pressing force that exists between the first groove outer side face and the first projection outer side face at room temperature. In any case, it is advantageous if a gap is maintained between the first groove inner side and the first projection inner side even at the mounting temperature.
In an advantageous embodiment of the rotor component, the rotor component has a cover section, by means of which the blade holding groove or the blade root of the rotor blade, which is fastened in the blade holding groove, can be covered at least in sections. For this purpose, the cover section needs to extend in the circumferential direction and in the radial direction. The cover section is arranged radially outside the first annular section groove. It is also proposed here that the cover section axially rests against the end face of the first rotor disk by means of a support surface in the region between the blade holding grooves.
In a particularly advantageous manner, it can be provided that the rotor components have cover sections on both sides, which are axially opposite each other.
At least, it is also advantageous if the support surface bears against the end face under compression when the cover section is elastically deformed. It is thus possible to ensure that: in any case, the support surface rests against the end surface when the fluid machine is operated at the operating temperature from rest up to the nominal rotational speed.
In order to achieve an advantageous pressing between the support surface and the end surface while avoiding an increase in the installation force, it can be advantageously provided that the rotor component is heated to an installation temperature between 100 ℃ and 200 ℃, which is accompanied by a deformation of the rotor component and in particular of the cover section, such that in a defined position of the rotor component relative to the fastening projection in the region of the annular groove, the pressing force between the support surface and the end surface corresponds to a maximum of 10% of the pressing force at room temperature. This state of deformation of the cover section in the axial direction, in particular in the region of the support surface, is achieved on the one hand by the configuration of the rotor component with the cover section arranged on the axial end. In addition, a configuration with a lower material thickness in the central region between the two annular grooves has an advantageous effect with respect to the desired deformation. On the other hand, the desired effect can be achieved by a targeted temperature increase, preferably in the region of the first annular groove.
Taking into account the possible mounting temperatures of the rotor components, the respective configuration of the rotor components, in particular the diameters of the first annular groove and the second annular groove and the overlap between the support surface and the end surface, is determined, on the one hand, without excessive effort, to enable the mounting and, during operation, the firm position of the rotor components between the rotor disks.
It is furthermore advantageous if, when the rotor component is mounted on the first rotor disk, a free first expansion distance is maintained between the first projection end face of the first fastening projection and the first groove bottom of the first annular groove. The first expansion distance is here at least 0.5mm. In contrast, the first expansion distance is disadvantageously greater than 5mm. Particularly advantageous are in particular first expansion distances of at least 1mm and at most 2.5mm.
It can also be provided that a second expansion distance is present between the second projection end face of the second fastening projection and the second groove bottom of the second annular groove. In this case, 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 respect to its fastening between two adjacent rotor disks results in a novel method for mounting the rotor.
A first rotor disk is first provided. In this case, it is advantageous if the first rotor disk is supported horizontally, with its rotor axis oriented vertically.
The rotor component must be heated to an installation temperature of at least 100 ℃ here or subsequently. In this case, the temperature should not exceed 200 ℃.
The rotor component is now mounted on the first rotor disk. For this purpose, the rotor component is placed on the first rotor disk such that the first annular groove is located above the first fixing projection. The rotor component can thus be pressed onto the first rotor disk until the support surface bears against the end face of the rotor disk.
By pushing the rotor member further onto the first rotor disk by means of an elastic deformation of the rotor member, a desired position of the rotor member relative to the rotor disk is reached, wherein the desired position is defined by a predefined first expansion distance between the first projection end face of the first fixing projection and the first groove bottom of the first annular groove.
Now, it is possible to cool the rotor component, wherein during this time the rotor component has to 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 onto the rotor member simultaneously. Here, the second fixing projection engages into the second annular groove.
Drawings
Exemplary embodiments of a rotor according to the present invention are drawn in the following figures. The drawings show:
fig. 1 schematically shows a rotor component between two rotor disks in a sectional view;
FIG. 2 shows a detail of the press fit between the first fixing projection and the first annular groove;
fig. 3 shows a detail of the gap between the second fixing projection and the second annular groove;
FIGS. 4-7 illustrate displacement of a rotor member relative to a rotor disk at startup of a gas turbine;
fig. 8-11 illustrate the mounting of the rotor member on the first rotor disk.
Detailed Description
The mounting of the rotor component 21 between the rotor disks 01 and 11 is schematically shown in fig. 1 in a sectional view. The rotor disks 01, 11 here each have blade holding grooves 02, 12 extending axially through the respective rotor disk 01, 11 so as to be distributed over the outer circumference. The blade holding slots 02, 12 are defined for receiving rotor blades. The respective rotor disk 01, 11 in turn has a respective fastening projection 04, 14 which surrounds the rotor axis 10. As can be seen, the fastening projections 04, 14 each extend axially to the opposite rotor disk. The rotor member 21 located between the two rotor disks 01, 11 covers the intermediate space located between the rotor disks 01, 11. For fastening, the rotor component 21 has annular grooves 24, 34 on axially opposite sides, respectively, into which annular grooves 24, 34 the respective fastening projections 04, 24 engage. Furthermore, at the axial end of the rotor component 21, a cover section 22 can be identified, which cover section 22 extends in the circumferential direction as well as in the radial direction. The cover section 22 here covers the blade holding groove 02 in the first rotor disk.
The details of the press fit between the first fixing projection 04 and the first annular groove 24 are drawn in fig. 2. For better visibility, the rotor component 21 is shown axially offset. The first rotor disk has a first projection outer side 05 on a radial outer side on the first fixing projection 04. The first projection inner side 06 is located on the diametrically opposite side. The first projection end face 07 is located on the free end of the first fixing projection 04. Similarly, the rotor member 21 has a first groove outer side 25 on the radially outer side and a first groove inner side 26 on the radially inner side on the first annular groove 24. The first groove bottom 27 is located opposite the first projection end face 07 on the annular groove 24. In the stationary state of the rotor at normal temperature, or after the rotor is mounted, there is a press fit between the first projection outer side face 05 and the first groove outer side face 25. The press fit is due to the geometrical overlap 08 between the two respective members 01, 21. On the diametrically opposite inner side, however, a gap 28 is present between the first projection inner side and the first groove inner side.
In fig. 3, the assembly between the second rotor disk 11 and the rotor component 21 is depicted in detail, wherein, similarly to fig. 2, the rotor component 21 is shown offset. Also identifiable is a second rotor disk 11 which basically has a blade holding slot 12 and a second fixing projection 14. The rotor disk 14 has a second convex outer surface 15 and a radially opposite second convex inner surface 16 on the radial outer side and a second convex end surface 17 on the end side. For this purpose, a second groove outer surface 35 and a second groove inner surface 36 are provided on the rotor component 21 on the second annular groove 34 radially outward and opposite to each other, and a second groove bottom 27 is provided opposite to the second projection end surface 17. It can be recognized that in the rest state or after assembly, gaps 09, 29 are present between the second fastening projection 14 and the second annular groove 34 on the radially outer side and on the radially inner side.
In the following fig. 4 to 7, the state of the rotor component 21 mounted on the two fastening projections 04, 14 is depicted when the gas turbine is started and the rotational speed increases to the setpoint rotational speed ωn and the temperature increases to the operating temperature TN.
The state after installation or in a stationary state is depicted in fig. 4 as described above. On the first rotor disk 01, there is a press fit on the radially outer side due to the overlap 08, whereas on the contrary there is a gap 28 on the radially inner side. Also, free gaps 09, 29 are present on both sides of the second fixing projection 14.
Fig. 5 now shows a first transitional state at the start-up of the gas turbine. If the rotor is now in motion, a first rotational speed ω1 is reached, which is still significantly lower than the target rotational speed ωn, wherein the component temperatures T01, 11, 21 of the rotor disks 01, 14 and of the rotor components can be increased slightly, but still away from the operating temperature TN. Importantly, in the first transitional state, the second groove inner side 36 now abuts the second projection inner side 16. Depending on the temperatures T01, 11, 21 of the components 01, 11, 21 and the existing gap 29 in the rest state, the contact is carried out at different rotational speeds, wherein the gap 29 is preferably set to a value which causes contact at a nominal rotational speed ωn of about 0.3 times.
As the rotational speed increases and the component temperature increases, the pressing force between the second fixing projection 14 and the rotor component 21 increases on the radially inner side, wherein the pressing force between the first fixing projection 04 and the rotor component 21 decreases on the radially outer side in contrast. In the second transitional state depicted in fig. 6, a gap now results between the first fastening projection 04 and the rotor component 21 on the radially outer side. That is, there is a free space between the first bump outer side 05 and the first groove outer side 25. In this state, the second rotational speed ω2 is located between the first rotational speed ω1 and the nominal rotational speed ωn in the first transitional state, wherein the second rotational speed ω2 can correspond to about 0.6 times the nominal rotational speed ωn. Because of the low mass of the rotor component 21 relative to the rotor disks 01, 11, the temperature increases more rapidly when the gas turbine is started. Accordingly, the component temperature T01, 11 of the rotor disks 01, 11 is significantly lower than the component temperature T21 of the rotor components, said component temperature T21 gradually approaching the operating temperature TN.
Fig. 7 shows the state when the rated rotational speed ωn and the operating temperature TN are reached. From the second transition state of the rotational speed increase, the first projection inner side 06 of the first fastening projection 04 rests against the first groove inner side 26 of the first annular groove 24.
The mounting of the rotor member 21 on the first rotor disk 01 is schematically shown in the following fig. 8 to 11. It is to be noted here that for advantageous installation, the rotor disk 01 is oriented vertically, rather than horizontally as shown here, and accordingly the rotor component 21 is located above the rotor disk 01. As mentioned above, it is proposed that there is an overlap 08 between the first projection outer side 05 of the first fixing projection 04 and the first groove outer side 25 of the first annular groove 24, so that a press fit is produced. It is furthermore proposed that the cover section 22 is pressed against the end face 03 of the rotor disk 01 by means of the support surface 23. This requires heating of the rotor member 21 for advantageous installation.
For this purpose, fig. 8 shows the state of the rotor disk 01 and the rotor member 21 located above it, wherein the rotor member 21 is previously heated to a temperature between 100 ℃ and 200 ℃. Thus on the one hand it is achieved that: the diameter of the first groove outer side 25 increases at least approximately to the diameter of the first projection outer side 05, whereby a pushing of the rotor component 21 onto the first fastening projection 04 can be achieved without excessive force.
However, another effect is achieved by the special shaping of the rotor member 21 upon heating. The effect is the following deformation of the rotor member 21: the cover section 22 is deformed away from the first rotor disk 01. Accordingly, the distance between the end face 03 and the support surface 23 increases, contrary to the case at room temperature.
For this purpose, fig. 9 shows the position of the rotor component 21 on the rotor disk 01 before the rotor component 21 reaches the abutment of the support surface 23 on the end surface 03. In this case, an increased expansion distance 33' remains between the first projection end face 07 and the first groove bottom 27.
The rotor component 21 is then pressed further onto the first fixing projection 04 of the first rotor disk 01 until the previously defined expansion distance 33 is reached, see fig. 10. The cover section 22 continues to deform, wherein an initial compression takes place between the support surface 23 and the end surface 03.
Fig. 11 now shows a state in which the rotor member 21 is cooled again from the desired position shown in fig. 10. It is noted here that the expansion distance 33 is kept constant. The temperature-induced deformation of the cover section 22 now remains as a geometry-induced deformation, with compression between the support surface 23 and the end surface 03. In this case, fig. 11 depicts a theoretical state with an overlap 13 between the rotor component 21 and the rotor disk 01.
List of reference numerals:
01 first rotor disk
02 first blade holding groove
03 end face
04 first fixing projection
05 first bulge outer side surface
06 the inner side of the first bulge
07 first convex end face
08. Overlapping
09 gap of
10 rotor axis
11 second rotor disk
12 second blade holding groove
13 overlap
14 second fixing projection
15 second convex outer side
16 second bump inner side
17 second raised end face
21 rotor component
22 cover section
23 support surface
24 first annular groove
25 first groove outer side surface
26 first groove inner side surface
27 first groove bottom
28. Gap of
29. Gap of
33. Expansion distance
34 second annular groove
35 second groove outer side
36 second groove inner side surface
37 second groove bottom.
Claims (17)
1. A rotor having
A first rotor disk (01), which first rotor disk (01) has a plurality of first blade holding grooves (02) which extend axially through the first rotor disk (01) and a circumferential, axially extending first fastening projection (04) which is arranged below the first blade holding grooves (02) on the side facing the rotor axis, and
a second rotor disk (11), which second rotor disk (11) is firmly connected to the first rotor disk (01) and has a plurality of second blade holding grooves (12) which extend axially through the second rotor disk (11) and a circumferential, axially extending second fastening projection (14) which is arranged below the second blade holding grooves (12) on the side facing the rotor axis, and
an annularly encircling rotor component (21), the rotor component (21) having an encircling, axially open first annular groove (24) on one side and an encircling, axially open second annular groove (34) on the opposite side, 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),
it is characterized in that the method comprises the steps of,
in a stationary state at room temperature
-a first groove outer side (25) of the first annular groove (24) bearing under compression against a first projection outer side (05) of the first fixing projection (04), and
-a gap is present between a first groove inner side (26) of the first annular groove (24) and a first projection inner side (06) of the first fixing projection (04).
2. The rotor of claim 1, wherein the rotor comprises a plurality of rotor blades,
in the rest state
-there is a gap between a second groove outer side (35) of the second annular groove (34) and a second projection outer side (15) of the second fixing projection (14), and
-there is a gap between a second groove inner side (36) of the second annular groove (34) and a second projection inner side (16) of the second fixing projection (14).
3. A rotor according to claim 2, wherein,
in a first transition state in which the first rotational speed is lower than the nominal rotational speed according to the specification,
-the first groove outer side (25) being in abutment with the first projection outer side (05), and
-there is a gap between the first groove inner side (26) and the first protrusion inner side (06), and
-there is a gap between the second groove outer side (35) and the second protrusion outer side (15), and
-said second groove inner side (36) is in abutment against said second protrusion inner side (16).
4. A rotor according to claim 3, wherein,
in a second transition state in which the second rotational speed is greater than the first rotational speed and less than the nominal rotational speed according to the specification,
-there is a gap between the first groove outer side (25) and the first protrusion outer side (05), and
-there is a gap between the first groove inner side (26) and the first protrusion inner side (06), and
-there is a gap between the second groove outer side (35) and the second protrusion outer side (15), and
-the second groove inner side (36) bearing against the second projection inner side (16) under compression.
5. The rotor of claim 4, wherein the rotor is at a rated rotational speed according to a specification
-a gap exists between the first groove outer side (25) and the first protrusion outer side (05),
-the first groove inner side (26) bearing under compression against the first projection inner side (06), and
-there is a gap between the second groove outer side (35) and the second protrusion outer side (15), and
-the second groove inner side (36) bearing against the second projection inner side (16) under compression.
6. The rotor according to claim 1 or 5, wherein,
at an installation temperature of at least 100 ℃ and at most 200 ℃ of the rotor member (21),
-the pressing force between the first groove outer side (25) and the first protrusion outer side (05) corresponds to a maximum of 10% of the pressing force at room temperature, and
-the pressing force between the first groove inner side (26) and the first protrusion inner side (06) corresponds to a maximum of 10% of the pressing force between the first groove outer side (25) and the first protrusion outer side (05) at room temperature.
7. A rotor according to any one of claims 1-5, characterized in that the rotor component (21) has a cover section (22) extending in the circumferential direction and radially, the cover section (22) covering the first blade holding grooves (02) at least in sections and bearing against the end face (03) of the first rotor disk in the region between the first blade holding grooves (02) by means of a bearing surface (23).
8. The rotor as set forth in claim 7, wherein,
the support surface (23) bears against the end surface (03) under compression with elastic deformation of the cover section (22).
9. A rotor according to claim 8, characterized in that the pressing force of the supporting surface (23) against the end face (03) corresponds to a maximum of 10% of the pressing force at room temperature at a mounting temperature of at least 100 ℃ and at most 200 ℃ of the rotor member (21).
10. The rotor according to any one of claim 1 to 5, wherein,
after mounting the rotor, at least before heating the rotor, a free first expansion distance exists between a first projection end face (07) of the first fixing projection (04) and a first groove bottom (27) of the first annular groove (24), wherein the first expansion distance is at least 0.5mm and at most 5mm.
11. The rotor as claimed in claim 10, characterized in that a free second expansion distance or abutment exists between the second projection end face (17) of the second fastening projection (14) and the second groove bottom (37) of the second annular groove (34), wherein the second expansion distance corresponds at most to 0.2 times the first expansion distance.
12. The rotor of claim 1, wherein the rotor is a gas turbine rotor.
13. A rotor according to claim 3, wherein the first rotational speed is between 0.2 and 0.6 times the rated rotational speed.
14. The rotor of claim 4, wherein the second rotational speed is at least 0.8 times the rated rotational speed.
15. The rotor as recited in claim 6, characterized in that a gap is present between the first groove inner side (26) and the first projection inner side (06).
16. The rotor of claim 10, wherein the first expansion distance is at least 1mm and at most 2.5mm.
17. A method for mounting a rotor according to any one of the preceding claims, the method comprising:
-providing a first rotor disc (01);
-heating the rotor member (21) to an installation temperature of at least 100 ℃ and at most 200 ℃;
-placing and/or pressing the rotor component (21) onto a first rotor disk (01), wherein a support surface (23) of the rotor component (21) rests against an end surface (03) of the first rotor disk (01);
-pushing the rotor member (21) further onto the first rotor disc (01) until a predefined expansion distance between a first projection end face (07) of a first fixing projection (04) and a first groove bottom (27) of the first annular groove (24) is reached;
-cooling the rotor member (21) and here holding the first rotor disc (01) and the rotor member (21) together;
-simultaneously placing and/or pressing the second rotor disc (11) onto the first rotor disc (01) and the rotor member (21).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201962916811P | 2019-10-18 | 2019-10-18 | |
| US62/916,811 | 2019-10-18 | ||
| PCT/EP2020/066858 WO2021073786A1 (en) | 2019-10-18 | 2020-06-18 | Rotor comprising a rotor component arranged between two rotor discs |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114599859A CN114599859A (en) | 2022-06-07 |
| CN114599859B true CN114599859B (en) | 2023-11-17 |
Family
ID=71266618
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202080073026.2A Active CN114599859B (en) | 2019-10-18 | 2020-06-18 | Rotor with rotor components arranged between two rotor disks |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP4013950B1 (en) |
| JP (1) | JP7394979B2 (en) |
| KR (1) | KR20220078706A (en) |
| CN (1) | CN114599859B (en) |
| WO (1) | WO2021073786A1 (en) |
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Also Published As
| Publication number | Publication date |
|---|---|
| WO2021073786A1 (en) | 2021-04-22 |
| KR20220078706A (en) | 2022-06-10 |
| EP4013950A1 (en) | 2022-06-22 |
| CN114599859A (en) | 2022-06-07 |
| EP4013950B1 (en) | 2023-11-08 |
| JP2022552170A (en) | 2022-12-15 |
| JP7394979B2 (en) | 2023-12-08 |
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