CN116146287A - Variable geometry turbine with adjustable stationary vanes having end honeycomb seal structure - Google Patents

Variable geometry turbine with adjustable stationary vanes having end honeycomb seal structure Download PDF

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Publication number
CN116146287A
CN116146287A CN202310138216.3A CN202310138216A CN116146287A CN 116146287 A CN116146287 A CN 116146287A CN 202310138216 A CN202310138216 A CN 202310138216A CN 116146287 A CN116146287 A CN 116146287A
Authority
CN
China
Prior art keywords
adjustable
face
stator blade
sealing structure
blade
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.)
Pending
Application number
CN202310138216.3A
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Chinese (zh)
Inventor
曹福堃
马正伟
吴明昊
张亮
唐富佳
冯百强
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703th Research Institute of CSIC
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703th Research Institute of CSIC
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Filing date
Publication date
Application filed by 703th Research Institute of CSIC filed Critical 703th Research Institute of CSIC
Priority to CN202310138216.3A priority Critical patent/CN116146287A/en
Publication of CN116146287A publication Critical patent/CN116146287A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention provides a variable geometry turbine with adjustable stator blades of an end honeycomb sealing structure, the adjustable stator blades are uniformly arranged along the circumferential direction of a hub, the upper end and the lower end of each adjustable stator blade are provided with rotating shafts, the rotating shafts at the upper end of each adjustable stator blade are connected with a linkage ring at the outer circumferential direction of the casing through mounting holes of the casing, the linkage ring adjusts the rotating angle of each adjustable stator blade, the rotating shafts at the lower end of each adjustable stator blade are arranged in a slot of the hub stator blade, grooves are formed at the upper end and the lower end of each adjustable stator blade, a honeycomb sealing structure is arranged in each groove, the honeycomb sealing structure at the upper end comprises an inner honeycomb sealing structure which forms the edges of a front groove and a rear groove by taking the rotating shafts as boundaries, and the honeycomb sealing structure at the lower end comprises an inner honeycomb sealing structure which forms the edges of the front groove and the rear groove by taking the rotating shafts as boundaries. The variable geometry turbine wide-working-condition variable geometry turbine can effectively reduce the leakage quantity of the gap at the end part of the adjustable stator blade, improve the aerodynamic efficiency of the variable geometry turbine and improve the stability of the variable geometry turbine in wide working condition operation.

Description

Variable geometry turbine with adjustable stationary vanes having end honeycomb seal structure
Technical Field
The invention relates to a turbine of a gas turbine, in particular to a variable geometry turbine with adjustable stationary blades with end honeycomb sealing structures, and belongs to the field of marine gas turbines.
Background
The marine gas turbine operates only 1.4% of the total annual operation time under the design working condition, and the fuel efficiency is reduced and the fuel consumption rate is sharply increased due to the fact that the fuel engine performance parameters are changed when the marine gas turbine is far away from the design working condition point. Therefore, variable geometry turbine technology has been developed to improve the matching relationship of the various components of the marine gas turbine to improve its wide operating performance. In order to ensure the rotation characteristics of the adjustable stator blade, gaps are reserved between the upper end wall and the lower end wall of the stator blade, and leakage loss is caused by the existence of end gaps, so that the turbine efficiency is affected. According to the prior art, it is desirable to provide variable geometry turbines that meet the wide operating performance of gas turbines while reducing tip clearance leakage losses of the adjustable vanes.
Disclosure of Invention
The invention aims to effectively improve the aerodynamic efficiency of a variable geometry turbine and designs the variable geometry turbine with the adjustable stationary blades of an end honeycomb sealing structure, which has high reliability.
The purpose of the invention is realized in the following way: the adjustable stator blades are uniformly distributed along the circumferential direction of the hub, the upper end and the lower end of each adjustable stator blade are provided with rotating shafts, the rotating shafts at the upper end of each adjustable stator blade are connected with a linkage ring at the outer circumferential direction of the casing through mounting holes of the casing, the linkage ring adjusts the rotating angle of each adjustable stator blade, the rotating shafts at the lower end of each adjustable stator blade are arranged in a hub stator blade slot, grooves are formed in the upper end part and the lower end part of each adjustable stator blade, a honeycomb sealing structure is arranged in each groove, the honeycomb sealing structure at the upper end part comprises an inner honeycomb sealing structure which forms the edges of the front groove and the rear groove by taking the rotating shafts as boundaries, and the honeycomb sealing structure at the lower end part comprises an inner honeycomb sealing structure which forms the edges of the front groove and the rear groove by taking the rotating shafts as boundaries.
Further, the upper end parts of the adjustable stator blades are spaced from the casing, and the lower end parts of the adjustable stator blades are spaced from the hub.
Further, the shaft diameter of the rotating shaft at the upper end part of the adjustable stationary blade is larger than that of the rotating shaft at the lower end part.
Further, grooves are arranged on the upper end face and the lower end face of the adjustable stationary blade along the edge of the blade by taking the rotating shaft as a boundary, and hexagonal grooves are arranged in the grooves on the upper end face and the lower end face of the adjustable stationary blade by taking the rotating shaft as a boundary. The thickness of the edge groove structure of the end part of the adjustable stator blade is 0.5-4% of the radial distance between the upper end surface and the lower end surface of the blade, the thickness of the hexagonal honeycomb sealing structure of the end part of the adjustable stator blade is 0.5-3% of the radial distance between the upper end surface and the lower end surface of the blade, the depth of the edge groove of the end part of the adjustable stator blade is 3-6% of the radial distance between the upper end surface and the lower end surface of the blade, the depth of the groove of the hexagonal honeycomb sealing structure of the end part of the adjustable stator blade is 2-5% of the radial distance between the upper end surface and the lower end surface of the blade, and the inner area of the groove of one hexagonal honeycomb sealing structure of the end part of the blade is 3-8% of the inner area of the groove of the end part of the adjustable stator blade.
Compared with the prior art, the invention has the beneficial effects that: based on the internal flow and loss distribution of the variable geometry turbine, the invention combines the simulation results of computational fluid dynamics software, increases the flow resistance of the gap of the end region through the adjustable stator blade end grooves and the honeycomb sealing structure, inhibits the leakage quantity of the gap of the end region, reduces the leakage flow loss of the gap, reduces the sensitivity of the variable geometry turbine to the gap height of the end region, and improves the wide working condition operation characteristic of the variable geometry turbine. In addition, the invention has reliable structure and can effectively ensure the practical application of engineering.
Drawings
FIG. 1 is a meridional view of the present invention;
FIG. 2 is a schematic view of an adjustable vane configuration with a honeycomb seal structure at the tip of the vane;
FIG. 3 is a view in the direction A of FIG. 1;
fig. 4 is a sectional view of B-B in fig. 3.
Detailed Description
The invention is described in further detail below with reference to the drawings and the detailed description.
In combination with FIG. 1The adjustable stator blade rotating shaft comprises a casing 1, adjustable stator blades 4 and a hub 7, wherein a rotating shaft 9 and a rotating shaft 10 are respectively arranged on an upper end face 8 and a lower end face 11 of each adjustable stator blade, the rotating shaft 9 of the upper end face of each adjustable stator blade is arranged in the casing 1, the rotating shaft 10 of the lower end face of each adjustable stator blade is arranged in the hub 7, the axes of the upper rotating shaft and the lower rotating shaft are positioned on the same rotating shaft axis, the rotating angle of each adjustable stator blade is convenient to control, the shaft diameter of the upper rotating shaft 9 is larger than that of the lower rotating shaft 19, and therefore the rotating process is reliable, and gaps are arranged between the upper end face 8 and the lower end face 11 of each adjustable stator blade and the casing 1 and the hub 7 respectively. W in the figure 1 To adjust the thickness of the end groove of the stator blade, W 2 For adjusting the thickness of the hexagonal honeycomb seal at the end part of the stator blade, H 1 To adjust the depth of the edge groove of the end part of the stator blade, H 2 The depth of the hexagonal groove of the honeycomb seal at the end part of the stator blade is adjustable, PS is the pressure surface of the blade, and SS is the suction surface of the blade.
Referring to fig. 2 to 4, the variable geometry turbine of the present invention having the adjustable vane with the end honeycomb seal structure is manufactured, and the adjustable vane of the turbine is designed using a conventional method. Based on given operating condition range and load distribution, structural parameters (end groove thickness W) of the adjustable stator blade with end honeycomb sealing structure are determined through simulation and test data of computational fluid dynamics simulation software 1 End honeycomb seal thickness W 2 End groove depth H 1 End honeycomb seal depth H 2 ). Thickness W of edge groove structures 2 and 6 at upper end and lower end of adjustable stator blade 1 The thickness W of the hexagonal honeycomb sealing structures 3 and 6 at the upper end and the lower end of the adjustable stator blade is 0.5-4% of the radial distance between the two end surfaces of the blade 2 0.5 to 3 percent of the radial distance between the two end surfaces of the blade; adjustable stator blade upper and lower end groove depth H 1 The radial distance between two end faces of the vane is 3 to 6 percent, and the depth H of the groove of the hexagonal honeycomb sealing structure at the upper end part and the lower end part of the adjustable stator vane is 2 The radial distance between two end faces of the blade is 2% -5%; the inner area of the groove of a hexagonal honeycomb sealing structure at the end part of the blade is 3-8% of the inner area of the groove at the end part of the adjustable stator blade. Those skilled in the art should comprehensively consider the design requirements of blade strength when designing a honeycomb seal structure,Processing difficulty, cost and other factors.
In summary, the invention aims to provide a variable geometry turbine with adjustable stator blades of an end honeycomb seal structure, which comprises a casing, a hub and adjustable stator blades, wherein the adjustable stator blades are uniformly arranged along the circumferential direction of the hub, the upper end and the lower end of each adjustable stator blade are provided with rotating shafts, the rotating shafts at the upper end of each adjustable stator blade are connected with a linkage ring at the outer circumferential direction of the casing through mounting holes of the casing, the linkage ring adjusts the rotating angle of each adjustable stator blade, the rotating shafts at the lower end of each adjustable stator blade are arranged in a slot of the hub stator blade, grooves are formed at the upper end and the lower end of each adjustable stator blade, a honeycomb seal structure is arranged in each groove, the honeycomb seal structure at the upper end comprises an inner honeycomb seal structure which forms the edges of a front groove and a rear groove by taking the rotating shafts as boundaries, and the honeycomb seal structure at the lower end comprises an inner honeycomb seal structure which forms the edges of the front groove and the rear groove by taking the rotating shafts as boundaries. The variable geometry turbine wide-working-condition variable geometry turbine can effectively reduce the leakage quantity of the gap at the end part of the adjustable stator blade, improve the aerodynamic efficiency of the variable geometry turbine and improve the stability of the variable geometry turbine in wide working condition operation.

Claims (9)

1. A variable geometry turbine with adjustable vanes having an end honeycomb seal structure, characterized by: the adjustable stator blades are uniformly distributed along the circumferential direction of the hub, the upper end and the lower end of each adjustable stator blade are provided with rotating shafts, the rotating shafts at the upper end of each adjustable stator blade are connected with a linkage ring at the outer circumferential direction of the casing through mounting holes of the casing, the linkage ring adjusts the rotating angle of each adjustable stator blade, the rotating shafts at the lower end of each adjustable stator blade are arranged in a groove of each hub stator blade, a honeycomb sealing structure is arranged at the upper end and the lower end of each adjustable stator blade, the honeycomb sealing structure at the upper end comprises an inner honeycomb sealing structure with the rotating shafts as the boundary to form front and rear groove edges, and the honeycomb sealing structure at the lower end comprises an inner honeycomb sealing structure with the rotating shafts as the boundary to form front and rear groove edges.
2. The variable geometry turbine with adjustable vane having an end honeycomb seal structure of claim 1, wherein: the upper end parts of the adjustable stator blades are spaced from the casing, and the lower end parts of the adjustable stator blades are spaced from the hub.
3. The variable geometry turbine with adjustable vanes of an end honeycomb seal structure of claim 1 or 2, wherein: the shaft diameter of the upper end part rotating shaft is larger than that of the lower end part rotating shaft.
4. The variable geometry turbine with adjustable vanes of an end honeycomb seal structure of claim 1 or 2, wherein: grooves are arranged on the upper end face and the lower end face of the adjustable stator blade along the edge of the blade by taking the rotating shaft as a boundary, the depth of the grooves is 0.5% -4% of the radial distance between the upper end face and the lower end face of the adjustable stator blade, and the thickness of the grooves is 3% -6% of the radial distance between the upper end face and the lower end face of the adjustable stator blade.
5. A variable geometry turbine with adjustable vanes of an end honeycomb seal structure as claimed in claim 3, wherein: grooves are arranged on the upper end face and the lower end face of the adjustable stator blade along the edge of the blade by taking the rotating shaft as a boundary, the depth of the grooves is 0.5% -4% of the radial distance between the upper end face and the lower end face of the adjustable stator blade, and the thickness of the grooves is 3% -6% of the radial distance between the upper end face and the lower end face of the adjustable stator blade.
6. The variable geometry turbine with adjustable vane having an end honeycomb seal structure of claim 4, wherein: a honeycomb sealing structure with hexagonal grooves is arranged in grooves on the upper end face and the lower end face of an adjustable stationary blade by taking a rotating shaft as a boundary.
7. The variable geometry turbine with adjustable vane of an end honeycomb seal structure of claim 5, wherein: a honeycomb sealing structure with hexagonal grooves is arranged in grooves on the upper end face and the lower end face of an adjustable stationary blade by taking a rotating shaft as a boundary.
8. The variable geometry turbine with adjustable vane of end honeycomb seal structure of claim 6, wherein: the thickness of the end hexagonal honeycomb sealing structure is 0.5-3% of the radial distance between the upper end face and the lower end face of the blade, the depth of the groove of the end hexagonal honeycomb sealing structure is 2-5% of the radial distance between the upper end face and the lower end face of the blade, and the inner area of the groove of one hexagonal honeycomb sealing structure is 3-8% of the inner area of the end groove of the adjustable stator blade.
9. The variable geometry turbine with adjustable vane of an end honeycomb seal structure of claim 7, wherein: the thickness of the end hexagonal honeycomb sealing structure is 0.5-3% of the radial distance between the upper end face and the lower end face of the blade, the depth of the groove of the end hexagonal honeycomb sealing structure is 2-5% of the radial distance between the upper end face and the lower end face of the blade, and the inner area of the groove of one hexagonal honeycomb sealing structure is 3-8% of the inner area of the end groove of the adjustable stator blade.
CN202310138216.3A 2023-02-20 2023-02-20 Variable geometry turbine with adjustable stationary vanes having end honeycomb seal structure Pending CN116146287A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310138216.3A CN116146287A (en) 2023-02-20 2023-02-20 Variable geometry turbine with adjustable stationary vanes having end honeycomb seal structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310138216.3A CN116146287A (en) 2023-02-20 2023-02-20 Variable geometry turbine with adjustable stationary vanes having end honeycomb seal structure

Publications (1)

Publication Number Publication Date
CN116146287A true CN116146287A (en) 2023-05-23

Family

ID=86355890

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310138216.3A Pending CN116146287A (en) 2023-02-20 2023-02-20 Variable geometry turbine with adjustable stationary vanes having end honeycomb seal structure

Country Status (1)

Country Link
CN (1) CN116146287A (en)

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