阅读说明：本技术 一种燃气轮机转子装置及应力调整方法 (Gas turbine rotor device and stress adjusting method ) 是由 张传斌 范玮 于 2021-10-13 设计创作，主要内容包括：本发明提供了一种燃气轮机转子装置,包括彼此啮合的第一和第二轮盘组件,各轮盘组件包括：轮盘；位于轮盘一侧的轴头；位于轮盘另一侧的整体轴段和端面齿；第一,第二轮盘组件通过端面齿的相互啮合传递压力与扭矩,整体轴段与端面齿之间还设有用于调节端面齿形表面应力的应力调整轴段,应力调整轴段的外径大于整体轴段的外径。本发明通过减小结构调整区域范围,基于尺寸的调整对象、调整范围与应力降低程度的关系,实现对端面齿的齿形表面应力的最佳调节效果。(The present invention provides a gas turbine rotor assembly comprising first and second disk assemblies enmeshed with each other, each disk assembly comprising: a wheel disc; a spindle nose located on one side of the wheel disc; the integral shaft section and the end face teeth are positioned on the other side of the wheel disc; first, the second rim plate subassembly passes through the intermeshing transmission pressure and the moment of torsion of terminal surface tooth, still is equipped with the stress adjustment shaft section that is used for adjusting terminal surface tooth surface stress between whole shaft section and the terminal surface tooth, and the external diameter of stress adjustment shaft section is greater than the external diameter of whole shaft section. The invention realizes the optimal adjustment effect on the tooth-shaped surface stress of the end face teeth by reducing the range of the structure adjustment area and based on the relationship between the adjustment object of the size, the adjustment range and the stress reduction degree.)

1. A gas turbine rotor assembly comprising first and second disk assemblies enmeshed with each other, each disk assembly comprising: a wheel disc (1); the shaft head (2) is positioned on one side of the wheel disc (1); the integral shaft section (3) and the end face teeth (4) are positioned on the other side of the wheel disc (1); first, second rim plate subassembly passes through the intermeshing transmission pressure and the moment of torsion of face tooth (4), its characterized in that, whole shaft section (3) with still be equipped with between face tooth (4) and be used for adjusting stress adjustment shaft section (5) of the profile of tooth surface stress of face tooth (4), the external diameter of stress adjustment shaft section (5) is greater than the external diameter of whole shaft section (3).

2. Gas turbine rotor arrangement according to claim 1, wherein a first ratio of an inner diameter of the stress adjustment shaft section (5) to an outer diameter of the stress adjustment shaft section (5) is smaller than a second ratio of an inner diameter of the monolithic shaft section (3) to an outer diameter of the monolithic shaft section (3).

3. The gas turbine rotor arrangement of claim 2, wherein the first ratio is in a range of 0.5 to 0.9.

4. The gas turbine rotor arrangement of claim 3, wherein the first ratio is in a range of 0.7 to 0.9.

5. Gas turbine rotor arrangement according to claim 1, characterized in that the stress adjusting shaft section (5) has an inner diameter equal to the inner diameter of the integral shaft section (3).

6. Gas turbine rotor arrangement according to claim 1, wherein the axial width of the stress adjustment shaft section (5) is smaller than the axial width of the monolithic shaft section (3).

7. A gas turbine rotor arrangement according to claim 6, wherein the ratio of the axial width of the stress adjustment shaft section (5) to the axial width of the integral shaft section (3) is in the range of 0.1-0.25.

8. Gas turbine rotor arrangement according to any of claims 1-7, characterised in that the diameter of the wheel disc (1), the outer diameter of the stress adjusting shaft section (5) and the outer diameter of the integral shaft section (3) decrease in the order named.

9. A gas turbine rotor arrangement according to any of claims 1-7, characterised in that the difference between the outer diameter and the inner diameter of the stress adjustment shaft section (5) is 2 times the tooth thickness h of the face teeth (4).

10. A gas turbine rotor arrangement according to claim 9, characterised in that the stress adjustment shaft section (5) has an outer diameter equal to the outer diameter of the face tooth (4).

11. A gas turbine rotor arrangement according to claim 10, wherein the tooth surface stress σ of the face tooth (4) satisfies the following equation:

σ＝(F+P)/h*t

f is an axial pressing force,

p is the circumferential pressure,

h is the tooth thickness of the face teeth (4),

t is the width of the tooth engagement surface (6).

12. A method of performing tooth surface stress adjustment of a face tooth using a gas turbine rotor apparatus according to any one of claims 1 to 11, comprising the steps of:

size adjustment step S1: adjusting a first ratio of an inner diameter to an outer diameter of the stress adjustment shaft section (5) for adjusting the tooth-shaped surface stress of the face tooth according to the size adjustment range;

stress determination step S2: determining a tooth form surface stress σ of the face tooth (4) based on the first ratio;

determination step S3: judging whether the tooth-shaped surface stress meets the design requirement or not;

if the tooth-shaped surface stress meets the design requirement, determining the size of the stress adjusting shaft section (5); if the design requirement is not met, repeating S1-S3 until the tooth surface stress meets the design requirement.

13. The method of adjusting tooth surface stress of a face tooth according to claim 12, wherein in the dimension adjusting step S1, the first ratio is in a range of 0.5 to 0.9.

14. The method of adjusting tooth surface stress of a face tooth according to claim 13, wherein in the dimension adjusting step S1, the first ratio is in a range of 0.7 to 0.9.

15. The method of tooth surface stress adjustment of a face tooth according to claim 14, wherein in the stress determining step S2, the tooth surface stress σ satisfies the following equation:

σ＝(F+P)/h*t

f is an axial pressing force,

p is the circumferential pressure,

h is the tooth thickness of the face teeth (4),

t is the width of the tooth engagement surface (6).

16. A gas turbine comprising a gas turbine rotor assembly according to any one of claims 1 to 11.

Technical Field

The invention relates to the technical field of mechanical transmission, in particular to a gas turbine rotor device and a stress adjusting method.

Background

The wheel disc end face teeth have high rigidity and self-centering performance, and have important application in rotor connection and torque transmission of heavy-duty gas turbines. Specifically, in the structure of the gas turbine, the face teeth are connected with the wheel discs of the adjacent stage by means of pressing force, so that the rotors are not separated and pressure and torque are transmitted. Generally, the pressing force requirement based on the tooth profile surface stress safety of the end face teeth and the pressing force requirement based on the non-separation of the rotor are contradictory, namely, a lower end face tooth pressing force is required to meet the tooth profile surface stress safety requirement of the end face teeth; in order to meet the safety requirement that the rotor is not separated, a higher pressing force is required. The manner of adjusting the pressing force is also often prone to insufficient adjustment safety margins.

In the prior art, under the condition that the rotor is not separated, the method for adjusting the tooth profile surface stress of the end face teeth generally adopts a mode of adjusting the inner and outer diameter sizes of the integral shaft section between the wheel disc and the end face teeth. The method has the defects that the size change of the integral shaft section causes large structural change area and large mass change, the strength and the rotor dynamic characteristic of the wheel disc of the gas turbine are influenced, and the tooth-shaped surface stress of the end face teeth cannot be adjusted in a targeted manner.

At present, a tooth surface stress of a wheel disc end face tooth connecting section under the action of pretightening force and torque is theoretically analyzed based on a certain circumferential pull rod rotor model disclosed in 'heat turbine' published in 2013, No. 1, No. 42, of China journal, and tooth surface stress of the wheel disc end face tooth connecting section is theoretically analyzed, a stamping model is provided for simulating tooth surface contact stress distribution, and comparison and verification are carried out on the method through a finite element method. The publication does not mention the scheme of adjusting the surface stress of the face tooth profile by adjusting the size of the inner diameter and the outer diameter of the rotor.

Also for example, CN208397163U discloses an easily replaceable wear-resistant wedge one-way transmission device, which comprises a first shaft member and a second shaft member, wherein when a wedge block is worn and failed, the first shaft member or the second shaft member is independently replaced, that is, a tooth and a shaft are manufactured into two detachable independent parts, so that the cost is reduced, and the structure design scheme is a structural design scheme for prolonging the service life. Nor is there any mention of adjusting the face tooth surface stress in this patent. In view of the foregoing, there is a need for a method of reducing the structural tuning area range to reduce the impact of mass and stiffness on strength and rotor dynamics and achieve optimal reduction of face tooth profile surface stresses.

The present invention has been made in view of the above problems.

Disclosure of Invention

The invention mainly aims to provide a gas turbine rotor device and a stress adjusting method, aiming at solving the defects in the prior art, and realizing the optimal adjusting effect on the tooth-shaped surface stress of end face teeth by reducing the range of a structure adjusting area and based on the relation between the size adjusting object, the adjusting range and the stress reduction degree, and simultaneously increasing the bending-resistant interface coefficient and reducing the risk of tooth meshing separation.

To achieve the above object, according to one aspect of the present invention, there is provided a gas turbine rotor apparatus including first and second disk assemblies enmeshed with each other, each disk assembly including: a wheel disc; a spindle nose located on one side of the wheel disc; the integral shaft section and the end face teeth are positioned on the other side of the wheel disc; the first wheel disc assembly and the second wheel disc assembly transmit pressure and torque through mutual meshing of the end face teeth, a stress adjusting shaft section used for adjusting tooth-shaped surface stress of the end face teeth is further arranged between the integral shaft section and the end face teeth, and the outer diameter of the stress adjusting shaft section is larger than that of the integral shaft section.

Further, a first ratio of the inner diameter of the stress adjustment shaft section to the outer diameter of the stress adjustment shaft section is smaller than a second ratio of the inner diameter of the integral shaft section to the outer diameter of the integral shaft section.

Further, the first ratio is in a range of 0.5 to 0.9.

Further, the first ratio is in a range of 0.7-0.9.

Further, the inner diameter of the stress adjustment shaft section is equal to the inner diameter of the integral shaft section.

To achieve the above object, according to one aspect of the present invention, there is provided a stress adjustment shaft section having an axial width smaller than that of a monolithic shaft section.

Furthermore, the ratio of the axial width of the stress adjustment shaft section to the axial width of the integral shaft section ranges from 0.1 to 0.25.

To achieve the above object, according to one aspect of the present invention, there is provided a method of sequentially reducing the diameter of a wheel disc, the outer diameter of a stress adjustment shaft section, and the outer diameter of an integral shaft section.

To achieve the above object, according to one aspect of the present invention, there is provided a stress adjustment shaft section having an outer diameter different from an inner diameter by 2 times a tooth thickness h of a face tooth.

Further, the outer diameter of the stress adjustment shaft section is equal to the outer diameter of the face tooth.

Further, the tooth form surface stress σ of the face tooth satisfies the following equation:

σ＝(F+P)/h*t

f is an axial pressing force,

p is the circumferential pressure,

h is the tooth thickness of the end face teeth,

t is the width of the tooth engaging surface.

In order to achieve the above object, according to an aspect of the present invention, there is also provided a method of performing face tooth surface stress adjustment of a gas turbine rotor device, including the steps of:

size adjustment step S1: according to the size adjusting range, adjusting a first ratio of the inner diameter to the outer diameter of a stress adjusting shaft section for adjusting the stress of the tooth-shaped surface of the end surface;

stress determination step S2: determining a tooth form surface stress sigma of the face tooth based on the first ratio;

determination step S3: judging whether the tooth surface stress meets the design requirement or not;

if the tooth surface stress meets the design requirement, determining the size of the stress adjustment shaft section; if the design requirement is not met, repeating S1-S3 until the tooth surface stress meets the design requirement.

Further, in the size adjusting step S1, the first ratio ranges from 0.5 to 0.9.

Further, in the size adjusting step S1, the first ratio ranges from 0.7 to 0.9.

Further, in the stress determining step S2, the tooth surface stress σ satisfies the following equation:

σ＝(F+P)/h*t

f is an axial pressing force,

p is the circumferential pressure,

h is the tooth thickness of the end face teeth,

t is the width of the tooth engaging surface.

In order to achieve the above object, according to an aspect of the present invention, there is also provided a gas turbine including the gas turbine rotor apparatus described above.

By applying the technical scheme of the invention, the stress adjusting shaft section for adjusting the stress of the tooth-shaped surface of the end surface is arranged, and the axial width of the stress adjusting shaft section is controlled so as to realize the adjustment of the stress of the tooth-shaped surface instead of the stress adjustment of the whole shaft section; based on the value range of the inner diameter and the outer diameter of the stress adjusting shaft section, the optimal effect of reducing the surface stress of the tooth profile is realized through the size adjustment of the inner diameter and the outer diameter, meanwhile, the bending-resistant section coefficient of the circular ring-shaped structure of the end face tooth is increased, the bending stress is reduced, and therefore the risk of tooth meshing separation is reduced.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 illustrates a schematic front view of a wheel disc assembly according to an embodiment of the present invention; and

FIG. 2 illustrates an isometric view of a wheel disc assembly according to an embodiment of the present invention; and

FIG. 3 illustrates a schematic front view of engagement of first and second wheel assemblies in accordance with an embodiment of the present invention; and

FIG. 4 illustrates an isometric view of the engagement of first and second wheel disc assemblies in accordance with an embodiment of the present invention; and

FIG. 5 shows a schematic of the tooth thickness and width of the tooth engaging face of a face tooth of an embodiment of the present invention.

Wherein the figures include the following reference numerals:

1. a wheel disc; 2. a shaft head; 3. an integral shaft section; 4. end face teeth; 5. a stress adjustment shaft section; 6. a tooth engaging surface; 7. a first wheel disc assembly; 8. a second wheel disc assembly.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

The present invention is described in further detail below with reference to specific examples, which are not to be construed as limiting the scope of the invention as claimed. The term "comprising" when used indicates the presence of a feature but does not preclude the presence or addition of one or more other features.

As shown in FIG. 1, a gas turbine rotor assembly generally includes first and second disk assemblies enmeshed with each other, the two disk assemblies being generally uniform in shape and size, each disk assembly comprising: a wheel disc 1; a spindle nose 2 positioned at one side of the wheel disc; an integral shaft section 3 and a face tooth 4 located on the other side of the wheel disc 1. The wheel disc assembly can be an integrated structure machined through integral forging, and can also be an assembly structure formed by separately machining and then assembling. The first and second wheel disc assemblies transmit pressure and torque through the mutual meshing of the face teeth 4. In general, the stress adjustment is carried out on the face teeth 4 of the wheel disc assembly by increasing the outer diameter of the integral shaft section 3, on one hand, the mode has larger influence on the mass distribution of the original structure of the wheel disc, the rigidity diameter change area is larger, and the influence on the rotor dynamic characteristic is larger; on the other hand, more optimal adjustment of the surface stress between the face teeth 4 cannot be achieved.

In order to solve the above problem, the present embodiment provides a gas turbine rotor apparatus, which includes, in addition to the above structure, a stress adjustment shaft section 5 provided between the integral shaft section 3 and the face teeth 4 for adjusting tooth-shaped surface stress of the face teeth, the stress adjustment shaft section 5 having an outer diameter larger than that of the integral shaft section 3. The ratio of the inner diameter to the outer diameter of the stress adjustment shaft section 5, namely a first ratio, exists between the inner diameter of the stress adjustment shaft section 5 and the outer diameter of the stress adjustment shaft section 5; there is a second ratio between the inner diameter of the monolithic shaft section 3 and the outer diameter of the monolithic shaft section 3. Preferably, the first ratio is greater than the second ratio. When the stress adjustment of the face tooth surface is performed by the stress adjustment shaft segment 5, the inner diameter and the outer diameter of the stress adjustment shaft segment 5 are adjusted mainly in accordance with the size adjustment range of the first ratio. Therefore, the first ratio is preferably in the range of 0.5 to 0.9. Further preferably, the first ratio is in the range of 0.7 to 0.9. The stress adjustment shaft section 5 and the monolithic shaft section 3 are preferably coaxial and have the same inner diameter.

In order to ensure that the influence of the mass distribution of the original structure of the wheel disc is small in the stress adjustment scheme and the tooth-shaped surface stress of the face teeth 4 is adjusted in a targeted manner, in the embodiment, the axial width of the stress adjustment shaft section 5 is smaller than that of the integral shaft section 3. Preferably, the ratio of the axial width of the stress adjustment shaft section 5 to the axial width of the integral shaft section 3 is in the range of 0.1-0.25. Preferably, the diameter of the wheel disc 1, the outer diameter of the stress adjusting shaft section 5 and the outer diameter of the integral shaft section 3 are reduced at once.

On the basis of the structure of the stress adjustment shaft segment 5, the present embodiment also provides a relationship between the size adjustment object based on the stress adjustment shaft segment 5 and the tooth surface stress. The tooth surface stress σ of the face tooth 4 satisfies the following equation:

σ＝(F+P)/h*t

f is an axial pressing force,

p is the circumferential pressure,

h is the tooth thickness of the face teeth 4,

t is the width of the tooth engaging surface 6.

As shown in fig. 5, tooth engaging surfaces 6 exist between the face teeth 4 of each wheel assembly, t is the width of the tooth engaging surface 6, and h is the tooth thickness of the face teeth 4. Preferably, the difference between the outer diameter and the inner diameter of the stress adjustment shaft section 5 is 2 times the tooth thickness h of the face tooth 4. Further preferably, the stress adjustment shaft section 5 has an outer diameter equal to the outer diameter of the face tooth 4.

The embodiment also provides a method for adjusting the tooth-shaped surface stress of the face teeth based on the gas turbine device, which comprises the following steps:

size adjustment step S1: and adjusting a first ratio of the inner diameter to the outer diameter of the stress adjustment shaft section for adjusting the tooth-shaped surface stress of the face tooth according to a size adjustment range, wherein the size adjustment range is a range of the first ratio, and preferably, the range of the first ratio is 0.5-0.9. Further preferably, the first ratio is in the range of 0.7 to 0.9, in which the degree of stress reduction and the sensitivity are highest, so that the tooth surface stress can be optimally reduced.

Stress determination step S2: based on the first ratio, a tooth form surface stress σ of the face tooth is determined. Specifically, the inner and outer diameter dimensions of the stress adjustment shaft segment are determined by the first ratio and are confirmed from the above dimensions by an equation satisfied by the tooth surface stress σ as follows:

σ＝(F+P)/h*t

f is an axial pressing force,

p is the circumferential pressure,

h is the tooth thickness of the face teeth 4,

t is the width of the tooth engaging surface 6.

Determination step S3: based on the above confirmation result, it is judged whether the tooth surface stress σ satisfies the design requirement.

If the tooth surface stress meets the design requirement, determining the size of the stress adjustment shaft section; if the design requirement is not met, repeating S1-S3 until the tooth surface stress meets the design requirement.

The embodiment also provides a gas turbine comprising the gas turbine rotor device.

From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects:

1. according to the gas turbine rotor device, the size of the stress adjusting shaft section connected with the tooth form of the end face tooth is adjusted, so that the influence of structural change on the mass distribution and the rigidity change area of the original structure of the wheel disc in the prior art is reduced, and the influence on the strength of the wheel disc and the dynamic characteristic of a rotor is reduced.

2. Compared with the prior art, the method for adjusting the stress on the tooth-shaped surface of the end face tooth through the size adjusting range of the inner-outer diameter ratio value of the stress adjusting shaft section has high stress reduction degree and sensitivity, and can realize the effect of optimally reducing the stress on the tooth-shaped surface.

3. The method for adjusting the tooth-shaped surface stress of the face teeth based on the stress adjustment shaft section can increase the bending section coefficient of the ring-shaped structure of the face teeth and reduce the bending stress, thereby reducing the risk of tooth meshing separation.

4. The invention only adjusts the size of the stress adjusting shaft section, particularly adjusts the outer diameter of the stress adjusting shaft section, and has small adjusting range, simple process scheme and easy operation.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.