CN210949254U - Rotor installation edge unloading structure with positioning and sealing functions - Google Patents
Rotor installation edge unloading structure with positioning and sealing functions Download PDFInfo
- Publication number
- CN210949254U CN210949254U CN201921226128.4U CN201921226128U CN210949254U CN 210949254 U CN210949254 U CN 210949254U CN 201921226128 U CN201921226128 U CN 201921226128U CN 210949254 U CN210949254 U CN 210949254U
- Authority
- CN
- China
- Prior art keywords
- bolt hole
- rotor
- groove
- mounting edge
- fan
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model relates to a rotor installation limit off-load structure with location and function of obturating, rotor installation limit off-load structure include with fan dish complex cap, the cap has the fitting surface be equipped with on the fitting surface a plurality of be used for with fan dish complex bolt hole and a plurality of runway groove between two adjacent connecting holes, runway groove extends along circumference, the runway groove can reduce bolt hole limit stress. The rotor mounting edge unloading structure can effectively reduce the stress of the mounting edge bolt hole edge, prolongs the service life of a rotor component of a gas turbine engine, and has a certain weight reduction effect.
Description
Technical Field
The application belongs to the technical field of gas turbine engines, and particularly relates to a rotor mounting edge unloading structure with positioning and sealing functions.
Background
At present, the mounting edge of the adjacent stage rotor of the gas turbine engine adopts a lotus edge unloading structure, and a typical mounting edge unloading structure is a fan-shaped notch penetrating through the inner diameter of the mounting edge, which is shown in fig. 1. The structure improves the service life of the engine by reducing the stress of the bolt hole at the mounting edge, and is an important technical means for solving the contradiction between high rotating speed, high temperature and high reliability of the modern gas turbine engine. However, when the rotor mounting edge has a radial matching spigot, the traditional unloading structure cannot meet the requirements of the concentricity and the sealing property of the rotor assembly.
As shown in fig. 2, a typical fan rotor mounting edge with a radial spigot positioning form is adopted, namely, a fan 1 and a cap cover 2 adopt a radial spigot positioning form, and the following problems exist in the connection structure if a traditional through unloading groove structure is adopted:
1) if an internal and external mixed unloading groove (namely the unloading groove on the fan disc mounting edge penetrates through the inner surface, and the unloading groove on the cap cover mounting edge penetrates through the outer surface, as shown in figure 3) is adopted, the flow channel is communicated with the disc cavity, and the gas in the engine flow channel flows back into the disc cavity to influence the pneumatic performance;
2) if the inner unloading grooves are adopted (namely, the fan disc and the cap mounting edge unloading grooves penetrate through the inner surface, see fig. 4a and 4b), the continuity of the seam allowance is damaged, the centering is influenced, and the problem of rotor vibration in the working process is caused.
Therefore, a new installation edge unloading structure is needed, and under the premise of effectively reducing the local stress of the installation edge bolt hole, the tight matching and gas sealing effects in the operation process of the installation edge seam allowance are guaranteed.
Disclosure of Invention
The present application is directed to a rotor mounting edge relief structure with locating and sealing features that solves or reduces at least one of the problems of the prior art.
The technical scheme of the application is as follows: the utility model provides a rotor installation limit off-load structure with location and function of obturating, rotor installation limit off-load structure include with fan dish complex bonnet, the bonnet has the fitting surface be equipped with on the fitting surface a plurality of be used for with fan dish complex bolt hole and a plurality of runway groove between two adjacent connecting holes, runway groove extends along circumference, runway groove can reduce bolt hole limit stress.
In the present application, the raceway grooves have an inner diameterR1And outer diameter R2The axial projection of the bolt hole falls on the inner diameter R1And outer diameter R2In the ring between.
In the present application, the raceway groove has a groove depth h in the axial direction, which is not less than 1/2 of the bolt hole depth.
In the present application, the raceway grooves have a fan angle θ, which is 240 °/m, where m is the number of bolt holes.
The rotor mounting edge unloading structure can effectively reduce the stress of the mounting edge bolt hole edge, prolongs the service life of a rotor component of a gas turbine engine, and has a certain weight reduction effect.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic view of a typical rotor mounting edge relief structure in the prior art.
Fig. 2 is a schematic view of a typical fan rotor connection structure in the prior art.
FIG. 3 is a schematic diagram of the connection of an internal and external mixing relief groove in the prior art.
Fig. 4 is a schematic view of an internal unloading groove in the prior art.
Fig. 5 is a front view of a relief structure of the present application.
Fig. 6 is a cross-sectional view of a relief structure of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
When the rotor mounting edge of the gas turbine engine works, the circumferential continuity of the structure is damaged by the connecting bolt holes, so that stress concentration is generated at the edges of the bolt holes, and the service life of the engine is influenced. The traditional inner diameter through type unloading groove is applied to an installation edge with a radial spigot, although the effects of reducing stress and prolonging service life can be realized, the circumferential continuity of the radial matching spigot can be damaged, the assembly concentricity of a rotor is further influenced, and the adoption of the inner and outer mixed type unloading grooves can cause the mutual mixing of a flow channel and disc cavity gas, and influence the performance of a fan and a secondary flow system. In order to guarantee structural connection stability and sealing effect, the application provides a rotor installation limit off-load structure and solves the life-span promotion problem of taking radial tang installation limit bolt hole.
The utility model provides a rotor installation limit off-load structure can be applied to in the off-load of fan and cap installation limit bolt hole, set up the runway groove 13 of a plurality of circular arc types at cap 10 and fan dish axial cooperation terminal surface 11, its quantity is unanimous with the quantity of bolt hole 12, runway groove 13 is along circumference equipartition, through the inside/outside diameter of control runway groove 13, degree of depth and fan-shaped angle, can realize the distribution adjustment of the hole limit circumferential stress of bolt hole 12 and off-load groove circumferential stress, finally realize reducing bolt hole limit stress under the condition that does not change tang cooperation area and obturage characteristic.
In the present application, the raceway groove 13 is substantially formed with a large outer diameter R2And a smaller inner diameter R1Parallel circumferential extensions form sectors with a diameter R at both edges2-R1Thereby forming the raceway groove 13. In some embodiments of the present application, it is ensured that the axial projection of the bolt hole 12 falls completely within the inner diameter R of the raceway groove 132And outer diameter R1Within the enclosed circle, i.e. point P as shown in figure 51And point P2The radius of the circle is R1≤R≤R2This allows the relief influence zone to cover all circumferential positions of the bolt hole.
As shown in fig. 6, in the present application, the axial depth of the unloading influence zone of the bolt hole 12 can be adjusted by the grooving depth h, and the grooving depth h is generally 1/2 which is not less than the depth of the bolt hole 12.
In the present application, the fan angle θ of the fan-shaped region may be used to adjust the stress distribution of the raceway groove 13 and the bolt hole 12, and the maximum stress of the two is equal to be optimal, or the fan angle θ may be 240 °/m, where m is the number of bolt holes.
This application effectively reduces installation limit bolt hole limit stress, promotes gas turbine engine rotor component life-span, has certain effect of subtracting weight simultaneously. The structure that this patent relates does not influence structural connection stability and obturage characteristic, does not have design space and technology restriction, easily realizes and the wide application.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (4)
1. The utility model provides a rotor installation limit off-load structure with location and function of obturating, a serial communication port, rotor installation limit off-load structure include with fan dish complex bonnet (10), bonnet (10) have fitting surface (11) be equipped with on fitting surface (11) a plurality of be used for with fan dish complex bolt hole (12) and a plurality of runway groove (13) between two adjacent bolt holes (12), runway groove (13) are followed circumference and are extended, runway groove (13) can reduce bolt hole (12) hole limit stress.
2. The rotor mounting edge relief structure according to claim 1 wherein said raceway groove (13) has an inner diameter R1And outer diameter R2The axial projection of the bolt hole (12) falls on the inner diameter R1And outer diameter R2In the ring between.
3. The rotor mounting edge relief structure according to claim 1 or 2, wherein said raceway groove (13) has a groove depth h in the axial direction, said groove depth h being not less than 1/2 of said bolt hole depth.
4. The rotor mounting edge relief structure according to claim 3 wherein said raceway groove (13) has a fan angle θ, said fan angle θ being 240 °/m, m being the number of bolt holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921226128.4U CN210949254U (en) | 2019-07-31 | 2019-07-31 | Rotor installation edge unloading structure with positioning and sealing functions |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921226128.4U CN210949254U (en) | 2019-07-31 | 2019-07-31 | Rotor installation edge unloading structure with positioning and sealing functions |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210949254U true CN210949254U (en) | 2020-07-07 |
Family
ID=71387195
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921226128.4U Active CN210949254U (en) | 2019-07-31 | 2019-07-31 | Rotor installation edge unloading structure with positioning and sealing functions |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210949254U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112211678A (en) * | 2020-10-16 | 2021-01-12 | 中国航发四川燃气涡轮研究院 | Long-life turbine rotor front baffle |
| CN114857142A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Connecting structure between different material members |
-
2019
- 2019-07-31 CN CN201921226128.4U patent/CN210949254U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112211678A (en) * | 2020-10-16 | 2021-01-12 | 中国航发四川燃气涡轮研究院 | Long-life turbine rotor front baffle |
| CN114857142A (en) * | 2022-05-12 | 2022-08-05 | 中国航发四川燃气涡轮研究院 | Connecting structure between different material members |
| CN114857142B (en) * | 2022-05-12 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | Connection structure between different material components |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN210949254U (en) | Rotor installation edge unloading structure with positioning and sealing functions | |
| CN111561480B (en) | Stator structure | |
| CN201496527U (en) | Combined piston ring with load-off grooves | |
| KR20160043914A (en) | Heat shield with centering features | |
| CN109779696B (en) | Open-hole rim sealing structure with flowing structure adaptability | |
| CN110805476B (en) | Turbine disc with cavity structure of obturaging | |
| CN103485951A (en) | Nozzle mounting and sealing assembly and method of mounting and sealing a nozzle assembly | |
| CN106979237A (en) | A kind of Leakproof shaft bearing | |
| US6632069B1 (en) | Step of pressure of the steam and gas turbine with universal belt | |
| CN111322480A (en) | High-durability rotary joint for wind power generation equipment | |
| CN113653537B (en) | Graphite seal shell with air guide groove and graphite seal device | |
| CN108952950A (en) | A kind of efficient turbocharger of highly integrated shafting | |
| CN210715961U (en) | Electric main shaft front end gas seal ring structure | |
| CN211819519U (en) | Turbine static disk, turbine and gas turbine | |
| CN109209672B (en) | Special-shaped valve seat ring bottom hole and cylinder cover | |
| CN210566889U (en) | Integral type reducing long shaft double-revolving-body central revolving joint | |
| CN205298771U (en) | Pneumatic valve actuator protector | |
| CN201041230Y (en) | Self-closed combined piston ring | |
| CN219412737U (en) | Sealing with positioning structure | |
| CN210660222U (en) | Nozzle ring positioning and sealing structure of mixed flow turbocharger | |
| CN109404060B (en) | Variable geometry mixed flow turbocharger sealing structure | |
| RU209925U1 (en) | High Power Turbine Rotor Assembly | |
| CN219587614U (en) | Steam sealing structure of steam turbine blade partition plate | |
| CN220151890U (en) | Carbon graphite ring shaft sealing structure | |
| US20210301681A1 (en) | Gas Turbine Component |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |