Damping ring for preventing nozzle abrasion, nozzle-swirler assembly and gas turbine
By adding a damping ring structure between the nozzle and the vortex generator in the gas turbine, the problem of nozzle wear was solved, resulting in extended nozzle life and stable operation of the gas turbine.
Patent Information
- Application Number
- CN202511693335.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-18
- Publication Date
- 2026-01-13
AI Technical Summary
Existing technologies struggle to suppress wear between nozzles and vortex generators in gas turbines, leading to deteriorated combustion performance, excessive emissions, and shortened lifespan of hot components.
By adding a ring-shaped damping ring structure between the nozzle and the vortex generator, vibration energy is absorbed and contact surface stress is reduced through the design of the petal structure and the selection of materials, thus suppressing high-frequency flutter.
It effectively reduces wear between the nozzle and the vortex generator, extends nozzle life, reduces maintenance costs, and improves the stable operating time of the gas turbine.
Smart Images
Figure CN121322983A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of gas turbine combustion chamber nozzle technology, specifically a damping ring to prevent nozzle wear, a nozzle-vortex assembly, and a gas turbine. Background Technology
[0002] During gas turbine operation, vibrations can occur due to rotor imbalance, shaft misalignment, and airflow excitation. These vibrations lead to fretting friction at the contact surfaces between the nozzles and the vortex generator, resulting in nozzle wear. Nozzle wear has many adverse effects on the normal operation of the gas turbine unit, such as deteriorated combustion performance, excessive emissions, and reduced lifespan of thermal components.
[0003] Current technologies for suppressing nozzle wear mainly include suppressing vibration sources, enhancing the wear resistance of the nozzle surface, and blocking transmission paths. Increasing the surface hardness of the nozzle through coatings and plating increases its lifespan, but this can easily transfer stress to other components, shortening their lifespan and exacerbating thermal fatigue in the vortex generator, making it prone to interface cracks during gas turbine start-stop cycles.
[0004] To address this problem, the present invention considers blocking the transmission path by adding a damping ring structure between the nozzle and the vortex generator. This consumes vibration energy through contact friction, reduces high-frequency flutter of the nozzle-vortex generator assembly, slows down the wear rate between the nozzle and the vortex generator, and improves the stable operating time of the gas turbine. Summary of the Invention
[0005] The purpose of this application is to provide a damping ring for preventing nozzle wear, a nozzle-vortex assembly, and a gas turbine, so as to solve the technical problem of difficulty in suppressing wear between the nozzle and the vortex in the prior art.
[0006] To achieve the above objectives, this application provides the following technical solution:
[0007] In a first aspect, this application proposes a damping ring for preventing nozzle wear, which is a ring-cylinder structure, comprising:
[0008] The body has multiple outwardly protruding petal-like structures;
[0009] The main body has a first end for fitting onto and fixing to the outer surface of the nozzle, and a second end for contacting the end face of the vortex generator, on both sides.
[0010] As a specific solution in the technical solution of this application, from the longitudinal section of the body, the petal structure is a U-shaped or V-shaped corrugated sidewall.
[0011] As a specific solution in this application, the body includes 3 to 5 consecutive petal-like structures.
[0012] As a specific solution in this application, the inner diameter of the petal-shaped structure gradually increases from the first end to the second end.
[0013] As a specific solution in this application, the outer diameter of the petal-shaped structure gradually increases from the first end to the second end.
[0014] As a specific solution in this application, the body wall thickness of the damping ring is 1 to 1.5 mm.
[0015] As a specific solution in this application, the damping ring is made of a nickel-based high-temperature alloy or a cobalt-based high-temperature alloy.
[0016] Secondly, this application also proposes a nozzle-vortex assembly, comprising: a nozzle, a vortex, and the aforementioned damping ring, wherein the nozzle passes through and is mounted on the vortex; a first end of the damping ring is fixedly connected to the nozzle, and a second end contacts the end face of the vortex.
[0017] As a specific solution in this application, the nozzle includes a nozzle rod and a nozzle head fixedly connected thereto, and the first end of the damping ring is fixedly connected to the nozzle rod.
[0018] As a specific solution in this application, the fixed connection is made by welding; optionally, the nozzle rod and the nozzle head are connected by argon arc welding, and the first end of the damping ring is connected to the nozzle rod by brazing.
[0019] Thirdly, this application proposes a gas turbine including the above-mentioned nozzle-vortex assembly.
[0020] Compared with the prior art, the beneficial effects of this application are:
[0021] 1. The nozzle-vortex assembly reduces the amplitude of vibration between the nozzle and the vortex by adding a damping ring structure, improves the dissipation of vibration energy between the nozzle and the vortex, reduces contact surface stress, inhibits nozzle wear, and extends nozzle wear life.
[0022] 2. Thermal deformation compensation: Multi-lobed damping ring structures, especially those with U-shaped or V-shaped corrugated sidewalls, can absorb a certain amount of thermal deformation in the axial and radial directions, achieving a passive thermal deformation adaptive adjustment effect.
[0023] 3. Reduced maintenance costs: Compared to replacing the entire nozzle, the replaceable damping ring design can significantly reduce production costs and has good economic benefits. Attached Figure Description
[0024] Figure 1 This is a cross-sectional schematic diagram of a nozzle-vortex assembly with a damping ring according to an embodiment of this application;
[0025] Figure 2 for Figure 1 The diagram shows an enlarged cross-sectional view of a nozzle-vortex assembly with a damping ring.
[0026] Figure 3 This is a front view schematic diagram of a damping ring proposed in an embodiment of this application;
[0027] Figure 4 for Figure 3 A schematic cross-sectional view of the damping ring along the AA direction.
[0028] The attached figures are labeled as follows:
[0029] 1- Nozzle rod;
[0030] 2-Edge converter;
[0031] 3-Damping ring; 31-First end; 32-Body; 33-Second end; 321-Leg-like structure;
[0032] 4- Nozzle head. Detailed Implementation
[0033] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.
[0034] It should be noted that in the description of this application, the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.
[0035] Furthermore, it should be understood that, where there is no conflict, features of the same embodiment and different embodiments of this application can be combined with each other.
[0036] It should also be understood that, for ease of description, the dimensions of the various components shown in the accompanying drawings are not drawn to actual scale; for example, the thickness or width of some layers may be exaggerated relative to other layers.
[0037] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined or described in one figure, it will not need to be discussed or described in detail in the description of the subsequent figures.
[0038] To address the technical problem of difficulty in suppressing wear between the nozzle and the vortex generator in the prior art, as mentioned in the background section, this application proposes an embodiment of a damping ring for preventing nozzle wear. Specifically, the damping ring 3 includes a body 32 with multiple outwardly protruding petal-shaped structures 321. The body 32 has a first end 31 on both sides for fitting onto and being fixedly connected to the outer surface of the nozzle, and a second end 33 for contacting the end face of the vortex generator.
[0039] like Figures 1-4 As shown, the damping ring 3 is generally a cylindrical structure. One end of the body 32 is the first end 32, a hollow cylindrical structure used to fit onto the outer surface of the nozzle and fix it to the nozzle. The connection method can be brazing, etc. The body 32 itself adopts a multi-lobed structure design, that is, it includes multiple corrugated sidewalls, each corrugation forming a lobe structure 321. In terms of its longitudinal cross-sectional shape, the lobe structure 321 is preferably a U-shaped or V-shaped corrugated sidewall. The other end of the body 32 is the free end, that is, the second end 33. After the nozzle and the vortex generator are fixedly installed, it contacts (fits) the end face of the vortex generator. Obviously, as... Figure 1-4 As shown, the second end 33 can be the end of the last petal-shaped structure of the body.
[0040] Preferably, the damping ring body 32 includes 3 to 5 consecutive petal-shaped structures. Figures 1-4 The image shown is of a damping ring with three consecutive lobed structures.
[0041] The damping ring body of this application adopts a U-shaped or V-shaped multi-lobed structure design, which can effectively constrain the micro-displacement of the nozzle head and avoid stress concentration caused by excessive constraint.
[0042] Preferably, from the first end 31 to the second end 32, the inner diameter of the petal-shaped structure 321 of the body 32 gradually increases; more preferably, the outer diameter of the petal-shaped structure 321 also gradually increases, see [reference needed]. Figure 2 and Figure 3 The gradually expanding design is mainly to prevent the damping ring from scratching the nozzle surface, and also to better fit the vortex generator surface, improving stability (larger contact area).
[0043] Preferably, the wall thickness of the damping ring 3 is 1 to 1.5 mm. Because the damping ring is relatively thin, during the operation of the gas turbine, the high-temperature thermal expansion difference generated by the U-shaped or V-shaped cross-section in the axial and radial directions can absorb thermal deformation, thus achieving a thermal expansion self-adaptive effect.
[0044] Preferably, the material of the damping ring 3 is a nickel-based high-temperature alloy, which matches the nozzle material and has good oxidation resistance, as well as excellent mechanical properties and corrosion resistance at high temperatures; it can also be a cobalt-based high-temperature alloy, which has better resistance to hot corrosion.
[0045] The damping ring 3 in this embodiment can limit the micro-displacement of the nozzle root, reduce the amplitude of fretting wear between the nozzle and the vortex generator, and effectively achieve damping and vibration reduction when vibration occurs.
[0046] This application also proposes a nozzle-vortex generator assembly, including a nozzle, a vortex generator 2, and a damping ring 3 as proposed in this application. The nozzle is mounted on the vortex generator 2. One side (first end 31) of the damping ring 3 is fixedly connected to the nozzle (e.g., by brazing), and the other side (first end 33) contacts the end face of the vortex generator 2 after the nozzle and vortex generator 2 are fixedly installed. Because the outer diameter of the damping ring 3 is small, it does not affect the disassembly and installation of the nozzle.
[0047] Preferably, the nozzle includes a nozzle rod 1 and a nozzle head 4 fixedly connected thereto. In some specific examples, the nozzle rod 1 and the nozzle head 4 are typically fixed by welding. A damping ring 3 is generally disposed on the nozzle rod 1.
[0048] During installation, such as Figure 1 As shown, firstly, the nozzle head 4 and nozzle rod 1 are fixedly connected by argon arc welding to form an integrated nozzle assembly structure. Secondly, the damping ring 3 is passed through the nozzle, and the first end 31 of the damping ring 3 is fixedly connected to the nozzle by brazing. Then, the nozzle is installed on the vortex generator (floating ring structure, adjustable up, down, left, and right), and the nozzle is fixed by the flange on the casing. Finally, the second end 33 contacts the end face of the vortex generator 2. When the gas turbine vibrates during operation, the contact friction between the free side of the damping ring 3 (i.e., the second end 33) and the vortex generator 2 can convert mechanical energy into heat energy, reducing the contact stress between the nozzle and the vortex generator 2, playing a damping and vibration reduction role, and suppressing nozzle wear caused by vibration. When the damping ring 3 needs to be replaced due to damage, the nozzle is first removed, the weld between the nozzle and the damping ring 3 is removed, and a new damping ring 3 is re-welded. Since the outer diameter of the damping ring 3 is small, it does not affect the disassembly and installation of the nozzle.
[0049] Meanwhile, since the damping ring 3 adopts a U-shaped or V-shaped cross-section design, the difference in axial / radial thermal expansion generated under high-temperature working conditions can absorb thermal deformation and play a role in thermal deformation compensation.
[0050] In the embodiments of this application, from the perspective of blocking the transmission path, a damping ring structure is added between the nozzle and the vortex generator. Vibration energy is consumed through contact friction, reducing the high-frequency flutter of the nozzle-vortex generator assembly, slowing down the wear rate between the nozzle and the vortex generator, and improving the stable operating time of the gas turbine. This has broad market prospects.
[0051] The nozzle-vortex assembly of the present application adds a damping ring. As a consumable part, the cost of replacing the damping ring separately is much lower than that of replacing the entire nozzle, which greatly reduces the production cost and has good economic benefits.
[0052] In practical applications, the vibration frequency and amplitude of the operating unit must first be measured, and several damping ring schemes with different interference fits must be designed. Based on the test results, the damping ring nozzle with the best wear suppression effect is selected. At this time, the damping coefficient of the damping ring is the optimal damping coefficient under this condition.
[0053] Although embodiments of this application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the appended claims and their equivalents.
Claims
1. A damping ring for preventing nozzle wear, characterized in that, It is a ring-shaped cylindrical structure, including: The body has multiple outwardly protruding petal-like structures; The main body has a first end for fitting onto and fixing to the outer surface of the nozzle, and a second end for contacting the end face of the vortex generator, on both sides.
2. The damping ring for preventing nozzle wear according to claim 1, characterized in that, Viewed in longitudinal section, the petal-like structure has U-shaped or V-shaped corrugated sidewalls.
3. The damping ring for preventing nozzle wear according to claim 2, characterized in that, The body comprises 3 to 5 consecutive petal-like structures.
4. The damping ring for preventing nozzle wear according to claim 2 or 3, characterized in that, From the first end to the second end, the inner diameter of the petal structure gradually increases, and / or the outer diameter of the petal structure also gradually increases.
5. The damping ring for preventing nozzle wear according to any one of claims 2-4, characterized in that, The thickness of the damping ring body wall is 1 to 1.5 mm.
6. The damping ring for preventing nozzle wear according to any one of claims 1-5, characterized in that, The damping ring is made of a nickel-based high-temperature alloy or a cobalt-based high-temperature alloy.
7. A nozzle-vortex generator assembly, characterized in that, include: The nozzle, the vortex generator, and the damping ring as claimed in any one of claims 1-6, wherein the nozzle passes through and is mounted on the vortex generator and is fixed; a first end of the damping ring is fixedly connected to the nozzle, and a second end contacts the end face of the vortex generator.
8. The nozzle-vortex generator assembly according to claim 7, characterized in that, The nozzle includes a nozzle rod and a nozzle head fixedly connected thereto, and the first end of the damping ring is fixedly connected to the nozzle rod.
9. The nozzle-vortex generator assembly according to claim 7 or 8, characterized in that, The fixed connection is made by welding; optionally, the nozzle rod and the nozzle head are connected by argon arc welding, and / or the first end of the damping ring is connected to the nozzle rod by brazing.
10. A gas turbine, characterized in that, Includes the nozzle-vortex assembly as described in any one of claims 7-9.