CN114876593B - Sealing structure for turbine rotor bearing cavity of core machine - Google Patents
Sealing structure for turbine rotor bearing cavity of core machine Download PDFInfo
- Publication number
- CN114876593B CN114876593B CN202210787928.3A CN202210787928A CN114876593B CN 114876593 B CN114876593 B CN 114876593B CN 202210787928 A CN202210787928 A CN 202210787928A CN 114876593 B CN114876593 B CN 114876593B
- Authority
- CN
- China
- Prior art keywords
- pressure
- sealing
- ring
- low
- shaft
- 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
Classifications
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- 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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the technical field of technical gas turbines, and particularly relates to a sealing structure for a turbine rotor bearing cavity of a core machine, which is used for replacing a low-pressure turbine rotor to be connected with the core machine and comprises a sealing shaft barrel and an oil cavity sealing bush; the sealing shaft barrel comprises a rear shaft section, a mounting disc part and a front shaft section; the rear shaft section, the mounting disc part and the front shaft section are arranged along the direction from back to front of the core machine; the front shaft section can extend into the long comb tooth ring, so that the long comb tooth ring and the high-pressure turbine shaft form a comb tooth seal; the front abutting surface of the mounting disc part can abut against the end surface of the rear side of the bearing oil injection ring, so that the third oil cavity is closed; a second oil chamber is formed among the oil chamber sealing bush, the turbine fulcrum frame and the sealing shaft barrel. The sealing structure can be adapted to the structure of the core machine, and has the advantages of simple structure, good manufacturability and low cost; and a sealing mode combining different seals is adopted, so that the sealing difficulty is reduced, and the change of an original structure is reduced.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a sealing structure for a turbine rotor bearing cavity of a core machine.
Background
A gas turbine is an internal combustion type power machine that converts energy of gas into useful work, and is widely used in the field of civil power generation or as a power device for use in airplanes or large ships. The working process of the gas turbine is as follows: the air compressor continuously sucks air from the atmosphere and compresses the air; the air before compression enters the combustion chamber, is mixed with the gas sprayed in the combustion chamber and is combusted before becoming high-temperature gas, then the high-temperature gas flows into the gas turbine to expand and do work, and the high-temperature gas is used for pushing the turbine to drive the gas compressor to rotate together; the gas turbine is a device with good cleaning performance and high efficiency, and has the advantages of small volume, low weight and the like.
The core engine is the heart of an aircraft engine, plays important roles in compressing air, generating heat through combustion and converting energy, is the worst part of the whole engine working environment and the parts with the highest temperature, the highest pressure and the highest rotating speed in an engine system, and therefore, the core engine test is of great importance in order to ensure the stability and the reliability of the engine. According to statistics, more than 80% of technical problems in the engine development process are closely related to the core machine, so the mastery degree of the core machine is the key for the success of the new engine development. Through the core machine test, not only can reduce the development risk of complete machine by a wide margin, can shorten the development cycle of complete machine moreover greatly.
The core mainly comprises a high-pressure compressor part, a combustion chamber and a high-pressure turbine part, and has extremely high working temperature and huge bearing load. In a gas turbine core test, the turbine components will tend to retain the high pressure turbine rotor and turbine fulcrum frame, while the low pressure turbine rotor is removed. However, because the test data of the core machine of the domestic gas turbine is less, the core machine is generally processed simply by removing the low-pressure turbine rotor and connecting the modified low-pressure shaft barrel with the turbine fulcrum frame, namely, the core machine test is started, so that a plurality of sealing structures and low-pressure bearings can be reserved, the structures are easy to reduce the stability and reliability of operation due to complex structures during the test, the core machine only has a high-pressure compressor to compress air, the internal air-entraining pressure of the core machine is far less than that of the whole machine, and therefore the sealing structures cannot meet the sealing requirements due to internal air-entraining, and at the moment, a connecting pipeline is needed to carry out external air-entraining; this not only inevitably leads to a series of problems of complex structure, increased cost, difficulty in machining and installation, etc., but also causes unpredictable disturbances to the core performance parameters under test. Therefore, a sealing structure for a bearing cavity of a high-pressure turbine rotor, which has a simple structure and reliable sealing, needs to be designed.
Disclosure of Invention
In order to solve the problem that after the low-pressure turbine rotor is disassembled during a core machine test, each bearing oil cavity is sealed, and the structural form during the core machine test is closer to the state when the low-pressure turbine rotor is reserved, the scheme provides a sealing structure for the bearing cavity of the core machine turbine rotor.
The technical scheme adopted by the invention is as follows:
a sealing structure for a turbine rotor bearing cavity of a core machine is used for replacing a low-pressure turbine rotor to be connected with the core machine;
the core machine comprises a turbine fulcrum frame, a high-pressure turbine shaft, a long comb tooth ring and a bearing oil injection ring; the turbine fulcrum frame is used as a support structure of the turbine rotor and is used for connecting and supporting the high-pressure turbine rotor and the low-pressure turbine rotor; a high-pressure rotor bearing is arranged between the turbine fulcrum frame and the high-pressure turbine shaft; a first oil cavity is communicated with one side of the high-pressure rotor bearing, which is close to the high-pressure turbine rotor; a third oil cavity is formed in one side, back to the high-pressure turbine rotor, of the high-pressure rotor bearing;
the sealing structure comprises a sealing shaft barrel and an oil cavity sealing bush;
the sealing shaft barrel comprises a rear shaft section, a mounting disc part and a front shaft section; the rear shaft section, the mounting disc part and the front shaft section are arranged along the direction from back to front of the core machine; the front shaft section can extend into the long comb tooth ring, so that the long comb tooth ring and the high-pressure turbine shaft form a comb tooth seal; the front side of the outer edge of the mounting disc part is provided with a front pressing surface which can be pressed on the end surface of the rear side of the oil injection ring of the bearing, so that the third oil cavity is closed;
the oil cavity sealing bush is in a conical ring shape, the rear side and the front side of the oil cavity sealing bush are respectively in sealing connection with the rear shaft section and the turbine fulcrum frame, and a second oil cavity communicated with the first oil cavity is formed among the oil cavity sealing bush, the turbine fulcrum frame and the sealing shaft barrel.
The structure can enable the core machine to be closer to the structural form of the low-pressure turbine rotor when the low-pressure turbine rotor is not disassembled in the test, and the sealing shaft barrel is used for replacing the low-pressure turbine shaft after the low-pressure turbine rotor is disassembled; the oil cavity sealing bush is used for replacing a low-pressure static grate toothed ring; the second oil chamber is replaced with a fourth oil chamber on the rear side of the low-pressure rotor bearing; the support in the long grate ring is ensured; ensuring the third oil chamber to be closed; and ensuring that the second oil chamber is communicated with the first oil chamber instead of the fourth oil chamber. The first oil chamber, the third oil chamber and the fourth oil chamber are original bearing chambers, and the first oil chamber, the second oil chamber and the third oil chamber are sealed bearing chambers of a sealing structure.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: the rear side of the oil cavity sealing bush is provided with an annular inner edge part, the annular inner edge part is sleeved on the outer side of the rear end of the rear shaft section, and the annular inner edge part and the rear end of the oil cavity sealing bush are sealed through a sealing ring.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: the rear end of the rear shaft section is connected with a fastening screw; the fastening screw is installed in the radial direction of the sealing shaft barrel and can press the annular inner edge part onto the rear shaft section.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: a tubular frame seat part is arranged on the inner side of the turbine fulcrum frame; the rear end of the frame seat part is in threaded connection with a large nut, and the large nut can tightly abut against a rear abutting surface on the rear side of the outer edge of the mounting disc part, so that sealing is formed between the front abutting surface and the oil injection ring of the bearing.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: the outer side of the rear end of the front shaft section is provided with a first convex part which is in interference fit with the inner side of the rear end of the long comb tooth ring; and a second convex part is arranged on the outer side of the front end of the front shaft section and is in interference fit with the inner side of the front end of the long comb tooth ring.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: a detachable clamping ring is further arranged on the outer side of the front end of the front shaft section; a step surface is arranged at the joint of the mounting disc part and the front shaft section; the long grate ring can be limited between the clamping ring and the step surface.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: the high-pressure turbine shaft is in a conical disc shape; the rear part of the inner edge of the high-pressure turbine shaft extends backwards and is tightly sealed with the rear part of the long labyrinth ring; the front part of the inner edge of the high-pressure turbine shaft extends forwards and is sealed with the front part grid teeth of the long grid tooth ring.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: a high-pressure movable grate toothed ring is arranged on the inner side of the backward extending part of the high-pressure turbine shaft, and a high-pressure static grate toothed ring is arranged on the turbine fulcrum frame; the high-pressure movable grate tooth ring and the high-pressure static grate tooth ring form a grate tooth seal to seal the first oil cavity.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: the front shaft section is tubular, a central disc portion is arranged on the inner wall of the middle portion of the front shaft section, an air guide hole is formed in the center of the central disc portion, an air guide channel is arranged on the front side of the air guide hole, and air can be guided to the labyrinth sealing portion of the first oil cavity through the air guide channel. The center of the sealing shaft barrel is provided with a hole so as to conveniently guide air into the core machine, and the sealing effect of the first oil cavity is better by utilizing air pressure.
As an alternative or complementary design to the above-described sealing structure for the core turbine rotor bearing cavity: the low-pressure turbine rotor comprises a low-pressure turbine shaft, a low-pressure movable grate toothed ring and a low-pressure static grate toothed ring; the low-pressure turbine shaft penetrates through the center of the turbine fulcrum frame and extends into the high-pressure turbine shaft; the low-pressure static grid toothed ring is fixed at the rear side of the turbine fulcrum frame and is tightly sealed and matched with the low-pressure movable grid toothed ring, and the low-pressure movable grid toothed ring is connected to a low-pressure turbine shaft; a low-pressure rotor bearing is arranged between the low-pressure turbine shaft and the turbine fulcrum frame; after the low-pressure turbine rotor is disassembled, the sealing shaft barrel replaces a low-pressure turbine shaft; the oil cavity sealing bush is used for replacing a low-pressure static grate toothed ring; the second oil chamber is substituted for a fourth oil chamber on the rear side of the low pressure rotor bearing.
The invention has the beneficial effects that:
1. when the structure in the scheme is used, the core machine can be closer to the structural form of the low-pressure turbine rotor when the low-pressure turbine rotor is not disassembled, and after the low-pressure turbine rotor is disassembled, the sealing shaft barrel is used for replacing a low-pressure turbine shaft; the oil cavity sealing bush is used for replacing a low-pressure static grate toothed ring; the second oil chamber is replaced with a fourth oil chamber on the rear side of the low-pressure rotor bearing; the support in the long grate ring is ensured; ensuring the third oil chamber to be closed; ensuring that the second oil chamber is communicated with the first oil chamber instead of the fourth oil chamber;
2. the sealing structure of the scheme can be more adaptive to the structure of a core machine, and has the advantages of simple structure (mainly embodied in that a series of structures below the sealing ring outer ring, the low-pressure turbine shaft, the low-pressure rotor bearing and the low-pressure rotor bearing are cancelled), good manufacturability (mainly embodied in that the front nut of the long comb tooth ring is cancelled and replaced by a snap ring due to complex processing of the comb tooth and the thread, the sealing of the comb tooth at the rear shaft section is changed into sealing of a rubber ring, the processing is simple and convenient), low cost, capability of remarkably improving the problems of complex structure and great process difficulty in the prior art, improvement on the stability and reliability of the system, and very high practical value and application prospect in the core machine test;
3. the sealing device is used for realizing the grate tooth sealing with the high-pressure turbine shaft by utilizing the original structure (long grate toothed ring) of the core machine, meanwhile, the sealing mode of the low-pressure movable grate toothed ring and the low-pressure static grate toothed ring is replaced by the sealing ring, and the sealing mode combining different seals is adopted, so that the sealing difficulty is reduced, the change of the original structure of the core machine is reduced, the existing bearing frame structure is fully utilized, and the sealing is kept on the premise of not changing;
4. the sealed shaft barrel structure in the scheme can effectively replace the action of a low-pressure turbine shaft, can effectively balance load and increase stability; in addition, the center of the sealing shaft barrel is provided with an opening so as to conveniently guide air into the core machine, and the sealing effect of the first oil cavity is better by utilizing air pressure.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below.
FIG. 1 is an exploded view of a seal for a turbine rotor bearing cavity of a core engine in this embodiment;
FIG. 2 is a schematic view of a partial cross-sectional structure of a sealing structure;
FIG. 3 is a block diagram of detail A of FIG. 2;
FIG. 4 is a state diagram of the seal structure in use;
fig. 5 is a structural view of the low-pressure turbine rotor when not detached.
In the figure: 1-a snap ring; 2-sealing ring; 3-oil cavity sealing bush; 31-annular inner edge portion; 4-sealing the shaft cylinder; 41-front shaft section; 411-second convex part; 412-a first projection; 42-a central disc portion; 421-air guiding hole; 43-mounting a disc portion; 431-front pressing surface; 432-rear pressing surface; 433 — step surface; 44-a rear shaft section; 441-third convex portion; 5-fastening screws; 6-long grate ring; 7-high pressure moving grate ring; 8-a high pressure turbine rotor; 9-a high pressure turbine shaft; 10-high pressure static grate ring; 11-a first oil chamber; 12-turbine fulcrum frame; 13-bearing oil spraying ring; 14-a second oil chamber; 15-a third oil chamber; 16-high pressure rotor bearings; 17-a first large nut; 18-a low pressure turbine rotor; 19-low pressure moving grate ring; 20-low pressure rotor bearings; 22-a fourth oil chamber; 23-low pressure static grate ring; 24-the outer ring of the seal ring.
Detailed Description
The technical solutions in the embodiments will be described clearly and completely with reference to the accompanying drawings, and the described embodiments are only a part of the embodiments, but not all embodiments, and all other embodiments obtained by those skilled in the art without creative efforts will belong to the protection scope of the present solution based on the embodiments in the present solution.
Example 1
The core mainly comprises a high-pressure compressor part, a combustion chamber and a high-pressure turbine part, and has extremely high working temperature and huge bearing load. In the performance of gas turbine core tests, the turbine components will tend to retain the high pressure turbine rotor 8 and turbine fulcrum frame 12, while the low pressure turbine rotor 18 is removed. In the prior art, after the low-pressure turbine rotor 18 is disassembled, a core machine is simply processed by adopting a method of connecting a modified low-pressure shaft cylinder with the turbine fulcrum frame 12, and then a core machine test is started, so that a plurality of sealing structures and low-pressure bearings are reserved, the running stability and reliability are reduced by the complex structures, the core machine only has a high-pressure compressor to compress air, the internal air-entraining pressure of the core machine is far less than that of the whole machine, and therefore the sealing structures cannot meet the sealing requirements by internal air-entraining and need a connecting pipeline to carry out external air-entraining; therefore, a series of problems of complex structure, increased cost, difficult processing and installation and the like are inevitably generated, and unpredictable interference is caused in the performance parameter test of the core machine.
In order to solve the above problems or some of the problems, the present embodiment designs a sealing structure for a turbine rotor bearing cavity of a core engine, as shown in fig. 1 to 4, the sealing structure includes a sealing shaft 4, an oil cavity sealing bush 3 and the like, and is used to connect with the core engine instead of a low-pressure turbine rotor 18.
In the core structure of the present embodiment, the low-pressure turbine rotor 18 is, before being disassembled, as shown in fig. 5, which includes the structure of the turbine fulcrum frame 12 and the connection between the turbine fulcrum frame and the high-pressure turbine rotor 8 and the low-pressure turbine rotor 18.
The high-pressure turbine rotor 8 comprises a high-pressure turbine shaft 9, and the high-pressure turbine shaft 9 is in a conical disc shape; the rear part of the inner edge of the high-pressure turbine shaft 9 extends backwards and is tightly sealed with the rear labyrinth of the long labyrinth ring 6; the front part of the inner edge of the high-pressure turbine shaft 9 extends forwards and is sealed with the front labyrinth of the long labyrinth ring 6. A high-pressure movable grate toothed ring 7 is arranged on the inner side of the backward extending part of the high-pressure turbine shaft 9, and a high-pressure static grate toothed ring 10 is arranged on a turbine fulcrum frame 12; the high-pressure movable grate toothed ring 7 and the high-pressure static grate toothed ring 10 form a grate seal to seal the first oil cavity 11. A tubular mount portion provided inside the turbine fulcrum frame 12; a high-pressure rotor bearing 16 is connected between the mount portion and the inside of the rearward extension of the high-pressure turbine shaft 9, and the first oil chamber 11 is located on the side of the high-pressure rotor bearing 16 toward the high-pressure turbine rotor 8, and this side communicates with the first oil chamber 11, thereby supplying lubricating oil to the high-pressure rotor bearing 16. A bearing oil injection ring 13 is arranged on the radial inner side of the turbine fulcrum frame 12, the bearing oil injection ring 13 is positioned on the inner side of the middle part of the frame seat part, a third oil cavity 15 is arranged on the right inner side of the bearing oil injection ring 13, and the third oil cavity 15 is also positioned on the side of the high-pressure rotor bearing 16, which faces away from the high-pressure turbine rotor 8; the bearing oil injection ring 13 can inject lubricating oil into the third oil chamber 15, thereby ensuring the smoothness of the rotation of the high-pressure rotor bearing 16.
The low-pressure turbine rotor 18 comprises a low-pressure turbine shaft, a low-pressure movable grate toothed ring 19, a low-pressure static grate toothed ring 23 and the like; the low-pressure turbine shaft can penetrate through the center of the turbine fulcrum frame 12 and extend into the high-pressure turbine shaft 9, at the moment, the long grate ring 6 is located between the low-pressure turbine shaft and the high-pressure turbine shaft 9, the low-pressure turbine shaft provides radial outward support for the long grate ring 6, and a large nut connected to the front end of the low-pressure turbine shaft is pressed against the end face of the long grate ring 6 backwards in the axial direction, so that the long grate ring 6 cannot generate axial displacement in the rotating process. A low-pressure rotor bearing 20 is provided between the rear portion of the mount portion inside the turbine fulcrum frame 12 and the low-pressure turbine shaft, the front side of the low-pressure rotor bearing 20 being opposed to the third oil chamber 15, thereby enabling the third oil chamber 15 to supply lubricating oil to the low-pressure rotor bearing 20; a large nut connected with the rear end of the frame seat part axially and forwards abuts against the low-pressure rotor bearing 20; a low-pressure static comb tooth ring 23 is fixedly arranged at the rear side of the turbine fulcrum frame 12, a low-pressure movable comb tooth ring 19 is sleeved at the outer side of the rear end of the low-pressure turbine shaft, the low-pressure static comb tooth ring 23 is in a conical ring shape, and meanwhile, the rear end of the low-pressure static comb tooth ring 23 is matched with the low-pressure movable comb tooth ring 19 to realize comb tooth sealing; inside the low-pressure static labyrinth ring 23, a fourth oil chamber 22 is formed in cooperation with the low-pressure turbine shaft and the turbine fulcrum frame 12, the fourth oil chamber 22 being capable of supplying lubricating oil to the low-pressure rotor bearing 20, and the fourth oil chamber 22 communicating with the first oil chamber 11 through a through hole in the turbine fulcrum frame 12, the through hole being located radially outside the pedestal portion.
After the low-pressure turbine rotor 18 is disassembled, the support in the long grate ring 6 is lost; the rear side of the third oil chamber 15 is open and cannot store lubricating oil; the fourth oil chamber 22 is removed from the low-pressure turbine rotor 18, and the first oil chamber 11 is communicated with the external air environment. Therefore, to reseal these locations and to bring the core closer to the non-disassembled configuration of low pressure turbine rotor 18 during testing, the sealing structure for the core turbine rotor bearing cavity of the present embodiment is designed. When the low-pressure turbine rotor 18 is not detached, the bearing cavities at the turbine fulcrum frame 12 are respectively a first oil cavity 11, a third oil cavity 15 and a fourth oil cavity 22; after the low-pressure turbine rotor 18 is disassembled and sealed by the sealing structure, the bearing cavities at the turbine fulcrum frame 12 are the first oil cavity 11, the second oil cavity 14 and the third oil cavity 15 respectively.
The sealing shaft barrel 4 comprises a rear shaft section 44, a mounting disc part 43 and a front shaft section 41; the rear shaft section 44, the mounting disc part 43 and the front shaft section 41 are arranged along the direction from back to front of the core machine; the front shaft section 41 can extend into the long grate ring 6, so that the long grate ring 6 and the high-pressure turbine shaft 9 form a grate seal; the front side of the outer edge of the mounting disc part 43 is provided with a front abutting surface 431, and the front abutting surface 431 can abut against the end surface of the rear side of the bearing oil injection ring 13, so that the third oil cavity 15 is closed; the oil cavity sealing bush 3 is in a conical ring shape, the rear side and the front side of the oil cavity sealing bush 3 are respectively connected with the rear shaft section 44 and the turbine fulcrum frame 12 in a sealing mode, and a second oil cavity 14 communicated with the first oil cavity 11 is formed among the oil cavity sealing bush 3, the turbine fulcrum frame 12 and the sealing shaft barrel 4. After the low-pressure turbine rotor 18 is disassembled, the sealing shaft barrel 4 is used for replacing a low-pressure turbine shaft; the oil cavity sealing bush 3 replaces a low-pressure static grate toothed ring 23; the second oil chamber 14 is substituted for the fourth oil chamber 22 at the rear side of the low pressure rotor bearing 20.
A large nut (i.e., the first large nut 17 in fig. 4) is screwed to the rear end of the frame seat portion, and the large nut can tightly abut against a rear abutting surface 432 on the rear side of the outer edge of the mounting disk portion 43, so that a seal is formed between the front abutting surface 431 and the bearing oil injection ring 13.
The rear side of the oil cavity sealing bush 3 is provided with an annular inner edge part 31, the annular inner edge part 31 is sleeved outside the rear end of the rear shaft section 44, and the annular inner edge part 31 and the rear end of the rear shaft section 44 are sealed through a sealing ring 2. The rear end outer side of the rear shaft segment 44 is convex radially outward, and forms a third convex portion 441.
The rear end of the rear shaft section 44 is connected with a fastening screw 5; the fastening screw 5 is mounted radially to the sealing shaft 4 and can press the annular inner rim 31 against the rear shaft section 44.
A first convex part 412 is arranged on the outer side of the rear end of the front shaft section 41, and the first convex part 412 is in interference fit with the inner side of the rear end of the long labyrinth ring 6; a second convex part 411 is arranged on the outer side of the front end of the front shaft section 41, and the second convex part 411 is in interference fit with the inner side of the front end of the long labyrinth ring 6.
The outer side of the front end of the front shaft section 41 is also provided with a detachable clamping ring 1; a step surface 433 is arranged at the joint of the mounting disc part 43 and the front shaft section 41; the long grate ring 6 can be limited between the clamping ring 1 and the step surface 433.
The front shaft section 41 is tubular, a central disc portion 42 is arranged on the inner wall of the middle portion of the front shaft section 41, an air guide hole 421 is arranged at the center of the central disc portion 42, an air guide channel is arranged on the front side of the air guide hole 421, and air can be guided to the labyrinth sealing portion of the first oil cavity 11 by the air guide channel. The center of the sealing shaft barrel 4 is provided with an opening to facilitate air entraining to the core machine, and the sealing effect of the first oil cavity 11 is better by utilizing air pressure.
Example 2
When the sealing structure is not used for the high-pressure turbine rotor 8 and the low-pressure turbine rotor 18 described in embodiment 1, but is applied to a core machine of other types or structures for sealing, the sealing structure may also be used for sealing.
Specifically, the sealing structure in this embodiment includes a rear shaft section 44, a mounting disc portion 43, and a front shaft section 41; the rear shaft section 44, the mounting disc part 43 and the front shaft section 41 are arranged along the direction from back to front of the core machine; the front side of the outer edge of the mounting disc part 43 is provided with a front pressing surface 431; the oil cavity sealing bush 3 is in a conical ring shape, the rear sides of the oil cavity sealing bush 3 are respectively connected with the rear shaft section 44 in a sealing mode, and a second oil cavity 14 is formed among the oil cavity sealing bush 3, the sealing shaft barrel 4 and the original structure of the core machine.
The rear side of the oil cavity sealing bush 3 is provided with an annular inner edge part 31, the annular inner edge part 31 is sleeved outside the rear end of the rear shaft section 44, and the sealing ring 2 is used for sealing between the annular inner edge part 31 and the rear end of the rear shaft section 44, so that the sealing scheme is simplified. The rear end of the rear shaft section 44 is connected with a fastening screw 5; the fastening screw 5 is mounted radially to the sealing shaft 4 and can press the annular inner rim 31 against the rear shaft section 44.
A first convex part 412 is arranged on the outer side of the rear end of the front shaft section 41, and the first convex part 412 is in interference fit with a corresponding part of the core machine; a second convex portion 411 is provided on the outer side of the front end of the front shaft segment 41, and the second convex portion 411 is in interference fit with a corresponding component of the core machine.
The outer side of the front end of the front shaft section 41 is also provided with a detachable clamping ring 1; a step surface 433 is arranged at the joint of the mounting disc part 43 and the front shaft section 41; so that the annular component acting like the long labyrinth ring 6 can be limited between the snap ring 1 and the step surface 433.
The front shaft section 41 is tubular, a central disc part 42 is arranged on the inner wall of the middle part of the front shaft section 41, an air guide hole 421 is arranged at the center of the central disc part 42, and an air guide channel is arranged on the front side of the air guide hole 421, so that air is guided to the labyrinth sealing part of the core machine, and the sealing effect is improved.
The above examples are merely for clearly illustrating the examples and are not intended to limit the embodiments; and are neither required nor exhaustive of all embodiments. And obvious variations or modifications of this technology may be resorted to while remaining within the scope of the technology.
Claims (8)
1. A seal structure for a core turbine rotor bearing cavity for connection to a core in place of a low pressure turbine rotor (18), characterized by:
the core machine comprises a turbine fulcrum frame (12), a high-pressure turbine shaft (9), a long comb tooth ring (6) and a bearing oil injection ring (13); the turbine fulcrum frame (12) is used for connecting and supporting the high-pressure turbine rotor (8) and the low-pressure turbine rotor (18); a high-pressure rotor bearing (16) is arranged between the turbine fulcrum frame (12) and the high-pressure turbine shaft (9); a first oil chamber (11) is communicated with one side of the high-pressure rotor bearing (16) close to the high-pressure turbine rotor (8); a third oil chamber (15) is arranged on one side of the high-pressure rotor bearing (16) back to the high-pressure turbine rotor (8);
the sealing structure comprises a sealing shaft cylinder (4) and an oil cavity sealing bush (3);
the sealing shaft barrel (4) comprises a rear shaft section (44), a mounting disc part (43) and a front shaft section (41); the rear shaft section (44), the mounting disc part (43) and the front shaft section (41) are arranged along the direction from back to front of the core machine; the front shaft section (41) can extend into the long grate ring (6) to enable the long grate ring (6) and the high-pressure turbine shaft (9) to form a grate seal; the front side of the outer edge of the mounting disc part (43) is provided with a front abutting surface (431), and the front abutting surface (431) can abut against the end surface of the rear side of the bearing oil injection ring (13) to enable the third oil cavity (15) to be closed;
the oil cavity sealing bush (3) is in a conical ring shape, the rear side and the front side of the oil cavity sealing bush (3) are respectively connected with the rear shaft section (44) and the turbine fulcrum frame (12) in a sealing mode, and a second oil cavity (14) communicated with the first oil cavity (11) is formed among the oil cavity sealing bush (3), the turbine fulcrum frame (12) and the sealing shaft barrel (4);
an annular inner edge portion (31) is arranged on the rear side of the oil cavity sealing bush (3), the annular inner edge portion (31) is sleeved on the outer side of the rear end of the rear shaft section (44), and the annular inner edge portion and the rear end of the oil cavity sealing bush are sealed through a sealing ring (2); a detachable clamping ring (1) is arranged on the outer side of the front end of the front shaft section (41); a step surface (433) is arranged at the connection part of the mounting disc part (43) and the front shaft section (41); the long comb tooth ring (6) can be limited between the clamping ring (1) and the step surface (433).
2. The seal structure for a core turbine rotor bearing cavity of claim 1, wherein: the rear end of the rear shaft section (44) is connected with a fastening screw (5); the fastening screw (5) is mounted radially to the sealing shaft sleeve (4) and can press the annular inner edge (31) against the rear shaft section (44).
3. The seal structure for a core turbine rotor bearing cavity of claim 1, wherein: a tubular frame seat part is arranged on the inner side of the turbine fulcrum frame (12); the rear end of the frame seat part is in threaded connection with a large nut which can tightly abut against a rear abutting surface (432) on the rear side of the outer edge of the mounting disc part (43) so as to form sealing between the front abutting surface (431) and the bearing oil injection ring (13).
4. The seal structure for a core turbine rotor bearing cavity of claim 1, wherein: a first convex part (412) is arranged on the outer side of the rear end of the front shaft section (41), and the first convex part (412) is in interference fit with the inner side of the rear end of the long labyrinth ring (6); a second convex part (411) is arranged on the outer side of the front end of the front shaft section (41), and the second convex part (411) is in interference fit with the inner side of the front end of the long grate tooth ring (6).
5. The seal structure for a core turbine rotor bearing cavity of claim 4, wherein: the high-pressure turbine shaft (9) is in a conical disc shape; the rear part of the inner edge of the high-pressure turbine shaft (9) extends backwards and is tightly sealed with the rear part labyrinth of the long labyrinth ring (6); the front part of the inner edge of the high-pressure turbine shaft (9) extends forwards and is tightly sealed with the front part labyrinth of the long labyrinth ring (6).
6. The seal structure for a core turbine rotor bearing cavity of claim 5, wherein: a high-pressure movable grate tooth ring (7) is arranged on the inner side of the backward extending part of the high-pressure turbine shaft (9), and a high-pressure static grate tooth ring (10) is arranged on the turbine fulcrum frame (12); the high-pressure movable comb tooth ring (7) and the high-pressure static comb tooth ring (10) form a comb tooth seal to seal the first oil cavity (11).
7. The seal structure for a core turbine rotor bearing cavity of claim 6, wherein: the front shaft section (41) is tubular, a central disc portion (42) is arranged on the inner wall of the middle portion of the front shaft section (41), an air guide hole (421) is arranged at the center of the central disc portion (42), an air guide channel is arranged on the front side of the air guide hole (421), and air can be guided to a labyrinth sealing portion of the first oil cavity (11) through the air guide channel.
8. The seal structure for a core turbine rotor bearing cavity of claim 1, wherein: the low-pressure turbine rotor (18) comprises a low-pressure turbine shaft, a low-pressure movable grate ring (19) and a low-pressure static grate ring (23); the low-pressure turbine rotor (18) penetrates through the center of the turbine fulcrum frame (12) and extends into the high-pressure turbine shaft (9); the low-pressure static comb tooth ring (23) is fixed on the rear side of the turbine fulcrum frame (12) and is in sealing fit with the low-pressure movable comb tooth ring (19), and the low-pressure movable comb tooth ring (19) is connected to a low-pressure turbine shaft; a low-pressure rotor bearing (20) is arranged between the low-pressure turbine shaft and the turbine fulcrum frame (12); after the low-pressure turbine rotor (18) is disassembled, the sealing shaft barrel (4) replaces a low-pressure turbine shaft; the oil cavity sealing bush (3) replaces a low-pressure static grate ring (23); the second oil chamber (14) is substituted for a fourth oil chamber (22) at the rear side of the low-pressure rotor bearing (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210787928.3A CN114876593B (en) | 2022-07-06 | 2022-07-06 | Sealing structure for turbine rotor bearing cavity of core machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210787928.3A CN114876593B (en) | 2022-07-06 | 2022-07-06 | Sealing structure for turbine rotor bearing cavity of core machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114876593A CN114876593A (en) | 2022-08-09 |
| CN114876593B true CN114876593B (en) | 2022-09-20 |
Family
ID=82683108
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210787928.3A Active CN114876593B (en) | 2022-07-06 | 2022-07-06 | Sealing structure for turbine rotor bearing cavity of core machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114876593B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115816071B (en) * | 2023-02-07 | 2023-04-28 | 成都中科翼能科技有限公司 | Assembling method of gas turbine supporting structure |
| CN116658304B (en) * | 2023-08-01 | 2023-10-20 | 成都中科翼能科技有限公司 | Bearing casing assembly of gas turbine shaft |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5160251A (en) * | 1991-05-13 | 1992-11-03 | General Electric Company | Lightweight engine turbine bearing support assembly for withstanding radial and axial loads |
| US5361580A (en) * | 1993-06-18 | 1994-11-08 | General Electric Company | Gas turbine engine rotor support system |
| US6619030B1 (en) * | 2002-03-01 | 2003-09-16 | General Electric Company | Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors |
| US6910863B2 (en) * | 2002-12-11 | 2005-06-28 | General Electric Company | Methods and apparatus for assembling a bearing assembly |
| CN205910008U (en) * | 2016-08-02 | 2017-01-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Load frame behind turbine of area cooling bleed |
| US10519860B2 (en) * | 2017-03-07 | 2019-12-31 | General Electric Company | Turbine frame and bearing arrangement for three spool engine |
| CN107084845B (en) * | 2017-04-21 | 2019-04-23 | 中国航发沈阳发动机研究所 | A kind of bearing bore of aero-engine high supercharging pressure level Fan Rig obturages system |
| CN107121289B (en) * | 2017-04-21 | 2019-04-23 | 中国航发沈阳发动机研究所 | A kind of bearing bore of aero-engine high supercharging pressure level Fan Rig obturages system |
| US11255221B2 (en) * | 2017-09-20 | 2022-02-22 | General Electric Company | Lube system for geared turbine section |
| CN111946464B (en) * | 2020-07-21 | 2021-09-07 | 中国科学院工程热物理研究所 | Flow guide blocking sealing structure for rear bearing cavity of high-pressure turbine disc |
| CN212454634U (en) * | 2020-09-04 | 2021-02-02 | 上海和兰透平动力技术有限公司 | Interstage sealing device for compressor and turbine rotor of small gas turbine |
| CN114542290A (en) * | 2020-11-26 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN113551039A (en) * | 2021-08-06 | 2021-10-26 | 中国科学院工程热物理研究所 | Self-adaptive graphite sealing structure for intermediate bearing cavity of aircraft engine |
| CN114526161B (en) * | 2022-04-22 | 2022-07-08 | 成都中科翼能科技有限公司 | Gas turbine's intermediary machine casket and reinforcement structure thereof |
| CN216894641U (en) * | 2022-06-01 | 2022-07-05 | 成都中科翼能科技有限公司 | Gas turbine bearing casing structure |
-
2022
- 2022-07-06 CN CN202210787928.3A patent/CN114876593B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN114876593A (en) | 2022-08-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114876593B (en) | Sealing structure for turbine rotor bearing cavity of core machine | |
| CN114526161A (en) | Gas turbine's intermediary machine casket and reinforcement structure thereof | |
| CN108019243B (en) | Turbine with integral bearing seat | |
| CN214366405U (en) | Multi-thrust-disc gas turbine capable of balancing axial force | |
| CN112555026B (en) | Multi-thrust disk gas turbine for balancing axial forces | |
| CN201723255U (en) | Assembled mechanical seal structure of screw rod expansion power machine | |
| CN101956571B (en) | Containerization type mechanical sealing structure of screw expansion power machine | |
| CN114060104A (en) | Stepped high-reliability long-life sealing structure for rotor of turbocharging system | |
| CN202360756U (en) | Sealing device of four-in-one set shaft | |
| CN220037035U (en) | Axial force balancing structure of impeller of air compressor | |
| CN207568660U (en) | A kind of intensive toe joint touch packing | |
| CN107355537B (en) | Carbon float sealing ring with fluid groove and sealing device thereof | |
| CN216714482U (en) | Shaft end sealing structure of supercritical high-back-pressure steam turbine | |
| CN220015274U (en) | Side tooth steam seal with vortex bottom cavity | |
| CN217652953U (en) | Solar thermal energy power generation high temperature molten salt pump middle bearing seat subassembly structure | |
| CN114033500B (en) | Rotor sealing structure of self-adaptive radial-flow turbocharging system | |
| CN215058144U (en) | Screw rod supercharging device | |
| CN215927476U (en) | Active vapor seal structure | |
| CN216767568U (en) | Gas bearing assembly and gas turbine | |
| CN216381634U (en) | Engine metal casting box | |
| CN219711596U (en) | Honeycomb steam seal structure for marine steam turbine | |
| CN218625433U (en) | Shaft end sealing structure of moving shaft | |
| CN220979916U (en) | Shaft end sealing structure of high-temperature fan | |
| CN211449168U (en) | Whole ring type metal inlaid floating ring seal with whole wave spring | |
| US11662024B2 (en) | Cartridge axial double-end-face split type mechanical seal |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |