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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/14—Form or construction
  • F01D5/141—Shape, i.e. outer, aerodynamic form
  • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
  • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• • 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
  • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
• • 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
  • F01D25/007—Preventing corrosion
• • 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
  • F01D5/12—Blades
  • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
  • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/31—Application in turbines in steam turbines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/32—Application in turbines in gas turbines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/60—Fluid transfer
  • F05D2260/602—Drainage
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/95—Preventing corrosion
• • 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
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the invention relates to the field of turbine and air compressor construction, more precisely to steam turbines as well as gas turbines and air compressor pressure stages, incorporating sealed shroud on turbine rotor blades, said seals located on shroud or incorporated in turbine stator.
• the invention can be used in the development of steam turbines at turbine manufacturing plants, as well as in enhancement of steam and gas turbines at heat power stations and that of aircraft engines with gas turbines and compressors.
• Shroud seals of a turbine stage consist as a rule of two ridges, with the first ridge 4 following the direction of steam flow located in the seal and the second ridge 5, both of which form a shroud chamber 11, located over the shroud, comprising radial clearances hi and h2, determining the flow rate of steam, coming through seal.
• Clearances hi and h2 are set equal in absolute value for each stage or stage group, said value depending on the conditions of thermal expansion of turbine parts, as well as on the conditions of turbo-unit threshold power, i.e. power, producing low frequency vibration.
• Rotor blade shroud 8 with layouts represented on Fig.3 and Fig.4 are in the form of a strip with openings 15 for rotor blade pins 9, which are unriveted after their mounting on rotor blades, forming a pack of six or more blades. Parts 13 of these shroud, covering single flow channel do not have any openings.
• the purpose of the invention is the improvement of steam and gas turbines operation reliability, the increase of actual efficiency factor and power as compared to the existing parameters.
• the abovementioned purpose is achieved by way of making of clearances hi and h2 in the ridges of shroud seals in such a manner, that the radial seal h2 on the second ridge 5 is smaller than the radial clearance hi on the first ridge 4, which permits to regulate the flow rate of steam, coming through shroud chamber 11 within specified limits.
• a system of discharge openings 12 is implemented in rotor blade shroud parts 13, covering single inter-blade channel, by way of drilling of the shroud Fig. 5 and Fig.6.
• the openings are located evenly along the surface of parts 13 and 14 of the shroud 8, following the direction of steam flow 18 Fig.4 in inter-blade channel 14. Said openings may be organized in staggered order 16, depending on the properties of deposits and their volume, as well as on seals design.
• the ratio between the number of openings n and their diameter d is the following:
• Sk is the square of the shroud's part, covering each single inter-blade channel in rotor wheel. Due to openings 12 in the shroud 8 of rotor blades 7 there occurs in the course of turbine operation a steam overflow from the chamber 11 located above the shroud and enclosure 17, also above the shroud Fig. 5 to the part of flow channel, located under the shroud, which leads to the creation of an obstacle effect, preventing the formation of metal and salt oxides on the inner surface of the shroud.
• the invention can be used for the following purposes: a) as means, preventing the formation of metal and salt oxides on the inner surfaces of rotor blade shrouds; b) as means for the enhancement of turbo-unit vibration state c) with the purpose of prolongation of period between repairs owing to p.p. a) and b) and that of turbine service life.
• the invention refers to the manufacture and operation of steam and gas turbines, compressed air plants and gas force pumps.
• Fig.l - a longitudinal section of turbine pressure stage with shroud seals in the nozzle block shield.
• Fig.2 - a longitudinal section of turbine pressure stage with shroud seals, located in rotor blade shrouds.
• Fig.3 - a shroud section of Fig.1;
• Fig.4 - a shroud section of Fig.2;
• Fig.5 - a detail of Fig.2 with section along D-D
• Fig.6 - a detail of F ⁇ g.l with section along C-C
• a steam (gas) turbine (compressor) pressure stage Fig.l and Fig.2. comprising a nozzle (directional) block 1 with nozzle (directional) blades 2 and a shield 3, seal shroud ridges 4 and 5 or ridges 4 and 5, located on the shroud 8 Fig.2 and rotor wheel with shroud 8, located on rotor blades 7 differs in the respect, that with the purpose of increasing the efficiency factor and operational reliability of turbine, radial clearance h2 of the second ridge 5 of shroud seal, located along the steam/gas flow is made less than radial clearance hi of the ridge 4 of the shroud seal and in parts 13,14,15 of the shroud 8, closing the single inter-blade channel there is a system of radial discharge openings 12 Fig.3., Fig.4, Fig.5 and Fig.6, distributed evenly in relation to the surfaces of parts 13, 14, 16 of shroud 8.
• Said radial discharge openings can also be organized in staggered order 16, as well as along medium steam flow line 14 and 18, or in symmetrical position to steam flow line 18 Fig.4 in the inter-blade channel, for steam (gas) overflow from the enclosure 17 above the shroud Fig.5 and chamber 11 above the shroud to the flow channel and the discharge of above shroud pressure, said pressure being the source of air dynamic above shroud and ridge "Thomas forces", which induce unstable operation of turbine rotor and its supports, whereas steam (gas), entering through the discharge openings 12 in shroud 8 to the above shroud enclosure of the flow channel prevents the formation of metal and salt oxides 10 on the inner surface of shroud 8 with the diameter d_of the openings 12 and their number n on each surface Sk of each flow channel of shroud parts 13,14, 16, covering the single inter-blade channel stand in the following ratio:

Landscapes

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

Applications Claiming Priority (1)

Publications (2)

Family

ID=33434336

Family Applications (1)

Country Status (10)

Citations (5)

Family Cites Families (8)

• 2003
  • 2003-04-18 JP JP2004571652A patent/JP4195882B2/ja not_active Expired - Lifetime
  • 2003-04-18 CA CA2562712A patent/CA2562712C/en not_active Expired - Fee Related
  • 2003-04-18 EP EP03726350A patent/EP1623097A4/de not_active Withdrawn
  • 2003-04-18 EA EA200501572A patent/EA008156B1/ru not_active IP Right Cessation
  • 2003-04-18 AU AU2003228590A patent/AU2003228590B2/en not_active Ceased
  • 2003-04-18 UA UAA200510908A patent/UA81314C2/uk unknown
  • 2003-04-18 CN CNB038266393A patent/CN100386502C/zh not_active Expired - Fee Related
  • 2003-04-18 WO PCT/US2003/012102 patent/WO2004099572A1/en active Application Filing
  • 2003-04-18 BR BRPI0318261-4A patent/BR0318261A/pt not_active IP Right Cessation
• 2006
  • 2006-12-05 HK HK06113323A patent/HK1092853A1/xx not_active IP Right Cessation

Patent Citations (5)

Non-Patent Citations (1)

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