US3306577A - Turbine device - Google Patents

Turbine device Download PDF

Info

Publication number
US3306577A
US3306577A US481008A US48100865A US3306577A US 3306577 A US3306577 A US 3306577A US 481008 A US481008 A US 481008A US 48100865 A US48100865 A US 48100865A US 3306577 A US3306577 A US 3306577A
Authority
US
United States
Prior art keywords
blades
rotor
turbine
blade
groups
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.)
Expired - Lifetime
Application number
US481008A
Other languages
English (en)
Inventor
Sagara Hideo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Application granted granted Critical
Publication of US3306577A publication Critical patent/US3306577A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers

Definitions

  • the present invention relates to a turbine rotor around the outer periphery of which a plurality of turbine blades are fastened radially, and more specifically to a turbine rotor to be driven by steam, gas or the like.
  • the blades of a steam or gas turbine are subject to a great centrifugal force and thrust due to the action of the working fluid.
  • the latter causes the blades to vibrate so that the blades must'be made of materials that can bear such vibration and the row of the blades must have a structure capable of withstanding resonant vibration.
  • it is very expensive to construct a turbine rotor with a strong structure and made of a material having high heat resistance and of vibration-resistant characteristics.
  • an object of the present invention is to eliminate the above mentioned disadvantages in a simple Way.
  • Another object of the present invention is to provide a turbine rotor wherein the row of the blades fastened radially around the outer periphery of a turbine rotor is divided into a plurality of groups of turbine blades whose tip portions are interconnected integrally and wherein the groups which are contiguous to each other have different numbers of turbine blades.
  • a further object of the present invention is to provide a turbine rotor made of a material which will not require special high characteristics in vibration resistance and in damping of vibration.
  • a still another object of the present invention is to provide a turbine rotor wherein excessive stress will not be produced at projecting portions of the blade roots even when a small number of blades in the blade groups are formed by interconnecting the tip portions of the successive blades in one row.
  • a still further object of the present invention is to provide a low cost turbine rotor the blades of which will not be damaged during operation.
  • FIG. 1 is a partial side view of an embodiment according to the invention
  • FIG. 2 is an enlarged view of FIG. 1 with the side of the rotor body broken away to show how the blades are fastened into an annular groove provided on the outer periphery of the rotor body,
  • FIG. 3 is a partial sectional view of the rotor body of FIG. 1 taken along line IIIIII of FIG. 1,
  • FIG. 4 is a front view of the turbine blade of FIG. 1,
  • FIG. 5 is a section taken along the line V-V of FIG. 4,
  • FIG. 6 is a partial sectional view of another embodiment of the present invention showing the turbine blades fastened into the rotor body
  • FIG. 7 is a partial side view of a still further embodiment of the invention illustrating the turbine blades being fastened into the rotor body from the lateral side thereof.
  • the rotor body of a steam turbine is generally represented by 1.
  • the turbine 1 is provided with an annular groove or recess 7 extending inwardly from the outer periphery of the rotor body.
  • the groove 7 includes a wide inner portion and an outer portion of less width formed between side projections 7'.
  • a turbine blade generally designated 2 and includes a foot or rootvportion 6 having a projection 6 at the extreme inner end of the root on each 1 side which engage at the bottom portion of the groove 7 of the rotor body and a stem 6 which fits between the projections 7' in the groove whereby loosening of the blades in relation to the rotor body 1 can be prevented.
  • each root 6 is successively fitted into the groove 7 so that each root 6 contacts the back of the root of the contiguous blade.
  • a plurality of blades 2 are fastened radially around the outer periphery of the rotor body 1.
  • the contact faces between the projections 6' of the blade root 6 and the projections 7 of the turbine rotor body 1 are provided with relief surfaces 6 inclined inwardly in the direction of the rotor body axis. Owing to such surfaces of relief 6 the upper surfaces of the projection 6 on the web side are prevented from contacting with the rotor body 1 directly below the projection 7.
  • a shroud 3 is joined to the tip portions of three turbine blades 2 by means of rivets 5 to form a group A.
  • a shroud 4 interconnects a group of blades B.
  • the blade groups A and B are alternately positioned around the whole circumference of the rotor body 1 within the annular groove 7 and the contiguous shrouds 3 and 4 are arranged in close abutting engagement of their end faces.
  • the contiguou groups of blades are subjectto different vibrations so that the vibration of the end blade of each group of blades is interferred with and damped by the vibration of the end blade of the contiguous group of blades.
  • the resonance of the blades is positively prevented.
  • the bending moment acting upon the blade 2 is received by the upper surface M of the backside of the blade root 6 and the lower surface N of the web side thereof, but the upper portion of the web side of the projection 6' is not subjected to the pressure force from the projection 7 because of the provision of the surface of relief 6 Consequently the corners 6 on the web side of the stem 6" of the blade root will not be subjected to great stress because of the surfaces of relief 6 but will only be subject to stresses due to a centrifugal force and a bending moment. Therefore cracks at the corner portions 6 can be prevented easily.
  • Each turbine blade has a sufiicient strength to bear impact due to partial admission of steam even when a smaller member of the blades are interconnected to form a blade group.
  • the numbers of the blade groups A and B are three and four, respectively, but the group of blades B may be replaced with a blade group consisting of a set of two blades the tip portions of which are interconnected by one shroud.
  • This can be accomplished because the mode and frequency of a blade group consisting of a set of two blades are different from those of the blade group A.
  • the factor of safety can be increased by very close contact of the tip portion of the backward blade of the blade group con- .sisting of the two blades with the tip portion of the forward blade of the contiguous blade. This provides a strength that corresponds to that of a blade group consisting of five blades.
  • the numbers of blades which are interconnected to form respective blade groups, which are alternately disposed may be four and six.
  • the numbers of blades in respective blade groups may be determined to be six and eight respectively.
  • a turbine blade can be produced, without being limited strictly by a calculated natural vibration, whereby the efiiciency of aturbine is increased and at the same time the dimension of a turbine rotor is reduced, resulting in decrease of the cost thereof.
  • FIG. 6 illustrates another embodiment of the invention and parts therein equivalent to those in the first embodiment are designated by the same reference numerals.
  • the rotor 1 is provided with a projection 7' and the blade is provided with a recess 6' for engagement on the projection.
  • FIG. 7 shows a still another embodiment of the invention and parts therein equivalent to those in the first embodiment are designated by the same reference numerals.
  • a plurality of projections 7 each having a Xmas tree-like contour and between them the roots 6 of the blades 2 are inserted from a lateral side of the rotor body 1 thereby to fasten blades 2 radially.
  • the blade groups interconnected by means of shrouds 3 and 4 in the circumferential direction of the rotor body 1 have alternately different numbers of turbine blades, for example, three blades, four blades or two blades. Therefore, there exists a great difference in mode and frequency of vibration between the blade groups and the blades 2, 2 which are located at the ends of the adjacent blade groups.
  • the abutting of the groups causes interference of such modes and frequencies directly or through the projections 7 on the rotor body so that the resonance of each blade can be prevented or suppressed.
  • the surface of relief 6 is provided at the uppermost portion of the web side of the projection 6' of the blade root which engages with the projection 7' of the turbine rotor even when the blade 2 may be deflected backwardly by the thrust of working fluid, the bending moment acting upon the blade is received by the upper surface M of the backside of the blade root and the lower surface N on the web side of the blade root, so that in this case on the upper portion of the web side of the blade root no great stress is produced, whereby a sufficient strength is given to the turbine blade, as in the first mentioned embodiment of this invention.
  • a turbine comprising a rotor having a recess defined around the periphery thereof, a plurality of turbine blades secured to the periphery of said rotor, each of said blades including a root portion engaged within the recess of said rotor, and shroud means interconnecting a plurality of said blades into a plurality of groups of blades extending around the periphery of said rotor, adjacent groups being of a different number of blades.
  • a turbine comprising a rotor having a recess do fined around the periphery thereof, a plurality of turbine blades secured to the periphery of said rotor, each of said blades including a root portion with a widened end engaged within the recess of said rotor, said widened ends of said blades having a relieved surface formed by an area of smaller dimension as a continuation of a sur face which bears radially outwardly against said rotor, and shroud means interconnecting a plurality of said blades into a plurality of groups of blades extending around the periphery of said rotor, adjacent groups being of a dif' ferent number of blades.
  • a turbine comprising a rotor having a recess defined around the periphery thereof, a plurality of turbine blades secured to the periphery of said rotor, each of said blades including a root portion with a widened end engaged within the recess of said rotor, said widened ends of said blades having a relieved undercut surface and a continuation surface which bears radially outwardly in respect to the rotor, and a peripheral shroud interconnecting the tips of a plurality of said blades into a plurality of groups of blades extending around the periphery of said rotor, said groups being in abutting relationship and the root portions of said blades being arranged in abutting relationship, at least some of said groups containing a different number of blades than the others of said groups.
  • a turbine comprising a rotor having a recess defined around its periphery extending radially inwardly and being widened at its inner end, a plurality of turbine blades having root portions with intermediate stems and widened inner ends arranged in the widened inner ends of said recesses, said widened inner ends being relieved at least along a portion of the area thereof at a location radially inwardly from its bearing engagement with said turbine rotor, a shroud interconnecting the outer tips of a plurality of said blades to form a first group of blades and interconnecting a plurality of tips of others of said blades to form a second group of blades, said first group having a different number of blades than said second group.
  • a turbine comprising a rotor having a recess defined around its periphery extending radially inwardly and being widened at its inner end, a plurality of turbine blades having root portions with widened inner ends arranged in the widened inner ends of said recesses, said widened inner ends being relieved at least along a portion of the area thereof at a location radially inwardly from its bearing engagement wit-h said turbine rotor, a shroud interconnecting the outer tips of a plurality of said blades to form a first group of blades and interconnecting a plurality of tips of others of said blades to form a second group of blades, said first and second groups being alternately arranged around the periphery of said rotor and being in abutting relationship, said first group having a different number of blades than said second group.
  • a turbine comprising a rotor having a substantially T-shaped recess defined around its periphery, a plurality of turbine blades having root portions with T-shaped ends engaged in the T-shaped recesses, said widened inner ends being relieved at least along a portion of the area thereof which is cut radially inwardly from its bearing engagement with said turbine rotor, a shroud interconnecting the outer tips of a plurality of said blades to form a first group of blades and interconnecting a plurality of tips of others of said blades to form a second group of blades, said first and second groups being alternately arranged around the periphery of said rotor and being in abutting relationship, said first group having a different number of blades than said second group.
  • a turbine comprising a rotor having a substantially T-shaped central projection extending around the periphery thereof, with a widened recess formed below each side of said T-shaped projection, a plurality of turbine blades having a substantially T-shaped recess positioned around said rotor blade with the recess engaged over the T-shaped projection, the blades having widened portions engaged in the widened portions of the recesses on said rotor, said blades having an undercut relief portion directly radially inwardly of each side of the T-shaped projection of said rotor, a shroud interconnecting the outer tips of a plurality of said blades to form a first group of blades and interconnecting a plurality of tips of others of said blades to form a second group of blades, said first and second groups being alternately arranged around the periphery of said rotor and being in abutting relationship, said first group having a different number of blades than said second group.
  • a turbine comprising a rotor having a recess defined around the periphery thereof, a plurality of turbine blades secured to the periphery of said rotor, each of said blades including a root portion engaged within the recess of said rotor, and shroud means interconnecting a plurality of said blades into a plurality of groups of blades extending around the periphery of said rotor including first and second groups, said first group being of a number which is 30 to of the number of the second group.
  • a turbine comprising a rotor having a recess defined around the periphery thereof, a plurality of turbine blades secured to the periphery of said rotor, each of said blades including a root portion engaged within the recess of said rotor, and shroud means interconnecting a plurality of said blades into a plurality of groups of blades extending around the periphery of said rotor, said groups being from 18 to 22 in number.
  • a turbine comprising a rotor having a recess defined around the periphery thereof, a plurality of turbine blades secured to the periphery of said rotor, each of said blades including a root portion with a widened end engaged with in the recess of said rotor, said widened ends of said blades having a relieved surface formed by an area of smaller dimension as a continuation of a surface which bears radially outwardly against said rotor, and shroud means interconnecting a plurality of said blades into a plurality of groups of blades extending around the periphery of said rotor, said relief surface being one sixth of the rotor bearing surface.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US481008A 1964-08-25 1965-08-19 Turbine device Expired - Lifetime US3306577A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP39048330A JPS5021603B1 (de) 1964-08-25 1964-08-25

Publications (1)

Publication Number Publication Date
US3306577A true US3306577A (en) 1967-02-28

Family

ID=12800390

Family Applications (1)

Application Number Title Priority Date Filing Date
US481008A Expired - Lifetime US3306577A (en) 1964-08-25 1965-08-19 Turbine device

Country Status (2)

Country Link
US (1) US3306577A (de)
JP (1) JPS5021603B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3584971A (en) * 1969-05-28 1971-06-15 Westinghouse Electric Corp Bladed rotor structure for a turbine or a compressor
US4386887A (en) * 1980-06-30 1983-06-07 Southern California Edison Company Continuous harmonic shrouding
US4710102A (en) * 1984-11-05 1987-12-01 Ortolano Ralph J Connected turbine shrouding
USRE32737E (en) * 1980-06-30 1988-08-23 Southern California Edison Continuous harmonic shrouding
US20040115059A1 (en) * 2002-12-12 2004-06-17 Kehl Richard Eugene Cored steam turbine bucket

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS58168867U (ja) * 1982-04-30 1983-11-10 日立化成工業株式会社 摩耗限度検出ブラシ
JPS58168866U (ja) * 1982-04-30 1983-11-10 日立化成工業株式会社 摩耗検知ブラシ

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1959220A (en) * 1933-05-26 1934-05-15 Gen Electric Rotary disk turbine bucket wheel, or the like
US2265592A (en) * 1939-01-16 1941-12-09 Allis Chalmers Mfg Co Turbine blade
US2308426A (en) * 1940-06-17 1943-01-12 Allis Chalmers Mfg Co Turbine blading
US2326145A (en) * 1941-03-18 1943-08-10 Westinghouse Electric & Mfg Co Turbine blade fastening
US2414278A (en) * 1943-07-23 1947-01-14 United Aircraft Corp Turbine blade mounting
US2431249A (en) * 1944-04-18 1947-11-18 Armstrong Siddeley Motors Ltd Securing projections to rotors
DE890803C (de) * 1943-02-19 1953-09-21 Aeg Befestigung der Deckbaender an den Turbinenschaufeln
FR1281536A (fr) * 1960-01-07 1962-01-12 Prvni Brnenska Strojirna Zd Y Rotor pour turbines ou autres applications et turbines munies de ce rotor ou rotor similaire

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1959220A (en) * 1933-05-26 1934-05-15 Gen Electric Rotary disk turbine bucket wheel, or the like
US2265592A (en) * 1939-01-16 1941-12-09 Allis Chalmers Mfg Co Turbine blade
US2308426A (en) * 1940-06-17 1943-01-12 Allis Chalmers Mfg Co Turbine blading
US2326145A (en) * 1941-03-18 1943-08-10 Westinghouse Electric & Mfg Co Turbine blade fastening
DE890803C (de) * 1943-02-19 1953-09-21 Aeg Befestigung der Deckbaender an den Turbinenschaufeln
US2414278A (en) * 1943-07-23 1947-01-14 United Aircraft Corp Turbine blade mounting
US2431249A (en) * 1944-04-18 1947-11-18 Armstrong Siddeley Motors Ltd Securing projections to rotors
FR1281536A (fr) * 1960-01-07 1962-01-12 Prvni Brnenska Strojirna Zd Y Rotor pour turbines ou autres applications et turbines munies de ce rotor ou rotor similaire

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3584971A (en) * 1969-05-28 1971-06-15 Westinghouse Electric Corp Bladed rotor structure for a turbine or a compressor
US4386887A (en) * 1980-06-30 1983-06-07 Southern California Edison Company Continuous harmonic shrouding
USRE32737E (en) * 1980-06-30 1988-08-23 Southern California Edison Continuous harmonic shrouding
US4710102A (en) * 1984-11-05 1987-12-01 Ortolano Ralph J Connected turbine shrouding
US20040115059A1 (en) * 2002-12-12 2004-06-17 Kehl Richard Eugene Cored steam turbine bucket

Also Published As

Publication number Publication date
JPS5021603B1 (de) 1975-07-24

Similar Documents

Publication Publication Date Title
US4936749A (en) Blade-to-blade vibration damper
US4130379A (en) Multiple side entry root for multiple blade group
US3377050A (en) Shrouded rotor blades
US3266771A (en) Turbines and compressors
US2999668A (en) Self-balanced rotor blade
US5154581A (en) Shroud band for a rotor wheel having integral rotor blades
US3326523A (en) Stator vane assembly having composite sectors
US3734646A (en) Blade fastening means
US3126149A (en) Foamed aluminum honeycomb motor
US3045968A (en) Fir tree blade mount
US5160242A (en) Freestanding mixed tuned steam turbine blade
US4710102A (en) Connected turbine shrouding
US5281097A (en) Thermal control damper for turbine rotors
US4743166A (en) Blade root seal
US5443367A (en) Hollow fan blade dovetail
US3918842A (en) Blade assembly for a fluid flow machine
US3014695A (en) Turbine bucket retaining means
US4076455A (en) Rotor blade system for a gas turbine engine
US3837761A (en) Guide vanes for supersonic turbine blades
US6371727B1 (en) Turbine blade tip shroud enclosed friction damper
US3424434A (en) Bladed rotor for a fluid flow machine,e.g. a gas turbine engine
US4969326A (en) Hoop shroud for the low pressure stage of a compressor
US4986737A (en) Damped gas turbine engine airfoil row
JPH0319881B2 (de)
US4460315A (en) Turbomachine rotor assembly