US2810544A - Gas turbine rotor - Google Patents

Gas turbine rotor Download PDF

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Publication number
US2810544A
US2810544A US237229A US23722951A US2810544A US 2810544 A US2810544 A US 2810544A US 237229 A US237229 A US 237229A US 23722951 A US23722951 A US 23722951A US 2810544 A US2810544 A US 2810544A
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US
United States
Prior art keywords
rotor
heat
spaces
gas
grooves
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
US237229A
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English (en)
Inventor
Schorner Christian
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.)
MAN AG
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg AG
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 MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Application granted granted Critical
Publication of US2810544A publication Critical patent/US2810544A/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21H—MAKING PARTICULAR METAL OBJECTS BY ROLLING, e.g. SCREWS, WHEELS, RINGS, BARRELS, BALLS
    • B21H1/00—Making articles shaped as bodies of revolution
    • B21H1/06—Making articles shaped as bodies of revolution rings of restricted axial length
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings

Definitions

  • This invention relates to certain improvements in regard to the thermal protection of steel rotors in gas turbines with high temperatures of the propellant gas.
  • the provision of ceramic blades is urged by the well-known'inferiority of metallic materials as regards creep strength, and also by the tendency of reducing to a minimum the loss of heat energy (e. g. by conduction into the metal rotor) which is suitable for the production of mechanical energy.
  • this task is solved in such a way that more particularly the superficies or surface portions of the rotor in front of and behind the blade-grids or stages are interrupted, by cutting grooves of a suitable cross section and depth, into comb-like strips, extending in an axial and/ or in a peripheral direction, depending on the local conditions such as direction of gas flow. These strips are shaped so that they are still in a reliable mechanical coherence with the rotor bodies. The upper ends of the walls between the grooves are then turned over, as by rolling, whereby cavities with practically stationary gas layers are obtained.
  • Patented Oct. 22, 1957 transmission of heat from the heated outer surfaces of the rotor to the supporting solid core thereof are reduced, by transverse and crosswise grooves, to cross sections in the form of thin studs.
  • the possibility of a flow of gas between the studs, which flow would impair the intended insulating effect, is practicallyeliminated by coating the studs with a ceramic or enamel layer by which the free space between the studs is greatly narrowed down. Owing to the spiral movement of the heating gas envelope around the rotor and by a corresponding direction of the grooves the formation of a convection current of the propellant gas within the narrow gaps left is avoided and thus a substantial reduction of the insulating effect of the layer is avoided. Owing to the fact that the studs are substantially unaffected by the mechanical strains within the carrier disc or drum a reliable durability of the heat insulating layer can be ensured if the expansion characteristics of the coating layer are approximately adapted to the data of the steel material.
  • Fig. 1 is a fragmentary axial section through a turbine rotor
  • Fig. 2 is an axial section through the heat-insulating layer 3 of a rotor, with the intermediate walls partly bent over,
  • Fig. 3 is an axial section through a modified form of heat insulating layer, with the intermediate walls partly bent over,
  • Fig. 4 is a plan view of a part of the rotor rim with longitudinal and transverse grooves
  • Fig. 5 is an axial or transverse section through one row of studs 13 of Fig. 4 showing a heat insulating layer having longitudinal and transverse grooves, and
  • Fig. 6 is a fragmentary plan view of the surface of the rotor of Fig. 1.
  • the heat insulating layers at the superficies of the disc or drum before and behind the blade grids or stages are denoted 3, and are illustrated as the form shown in'Fig. 2.
  • an axial boring 18 is provided in the rotor from which radial passages 19 branch off and open into an axial groove 20 at the rotor surface covered by cover plate 21.
  • the circumferential grooves or spaces 6 open into the axial groove 20 so that a coolant may be circulated through the groove 6 by being introduced into axial boring 18 and, thence, through radial channels 19 to groove 20.
  • these insulating layers are formed by annular grooves 4 worked into the surface, the outer portions of the intermediate walls 5 between these grooves being bent over to form hollow spaces 6 containing either a stagnant gas layer or being traversed by cooling air.
  • the intermediate walls 7 are provided with two brims or tabs 8 and 9 which are bent over to opposite sides and together with thetabs 8 and'9 of 'tlieadjacent walls form the upper closure ofthe hollow spaces 10.
  • the grooves and the hollow spaces 6, or 10 extend transveresly to the longitudinal axis of 'the "rotor or "parallel thereto and across-the direction of-gasfiow.
  • the production 'of the"heat'-insuiating' layer according tothe invention is very "simple-and'oiferstheadvantage that loose screening elements are avoided whose. reliable fastening on the rotor is oftentimes very'difiicult'owing' to the high speeds.
  • a high temperature gas turbine having a metal rotor with a plurality of stages of turbine blades thereon and in which the surface of said rotor between said adjacent stages is directly exposedto high temperature gas flow through said turbineyasheat insulating layer for said exposed surface of said rotor between said adjacent stages comprising a plurality of thin projections on said exposed rotor surface-definingitherebetweena plurality :of circumferential annular grooves forming insulating gas spaces .
  • the radially outer portions of said 1 projections forming at least "a partial closure at said spaces to reduceaerodynamic ilowrresistance thereof, the radially inner portions of said spaces defining a heat insulating layer interposed between said high temperature gasflow -and.said rotor, and means .forsupplying a heat insulating coolant into said spaces.
  • heat insulatinglayer for said exposed surfaceofisaid rotorbetweensaid adjacent stages comprising a plurality ofithinprojectionson said exposed rotor surface defining therebetweena plurality of circumferential annular, grooves .iorming insulating .gas spaces for reducing heat conductionfrom.saidhightemperature gas "flow tosaid rotor, the radially .outer portions of said projections forming at least .a partial .closurefor said spaces to reduce aerodynamicflowrresistance thereof, the radially innerportions .of saidflspaces defining a heat insulatinglayerinterposed'vbetweensaid high temperature gasfiowfand sai d rotor,,and passagemeans through said partial closure communicating between said spaces and the. outer surface of said .closurejfor passage of low l temperature gasiromrsaidspaces to "form. a heat insulating layer over the outer surface .otseiid rotor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US237229A 1951-01-20 1951-07-17 Gas turbine rotor Expired - Lifetime US2810544A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEM8293A DE943328C (de) 1951-01-20 1951-01-20 Waermeschutzeinrichtung fuer den staehlernen Laeufer einer Gasturbine mit hohen Treibmitteltemperaturen

Publications (1)

Publication Number Publication Date
US2810544A true US2810544A (en) 1957-10-22

Family

ID=7294107

Family Applications (1)

Application Number Title Priority Date Filing Date
US237229A Expired - Lifetime US2810544A (en) 1951-01-20 1951-07-17 Gas turbine rotor

Country Status (3)

Country Link
US (1) US2810544A (de)
CH (1) CH295196A (de)
DE (1) DE943328C (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2996280A (en) * 1959-04-07 1961-08-15 Iii John A Wilson Heat shield
US3055633A (en) * 1957-04-19 1962-09-25 Pouit Robert Hot gas turbines
US5507620A (en) * 1993-07-17 1996-04-16 Abb Management Ag Gas turbine with cooled rotor
US20030101730A1 (en) * 2001-12-05 2003-06-05 Stefan Hein Vortex reducer in the high-pressure compressor of a gas turbine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US702461A (en) * 1901-12-19 1902-06-17 Johannes Nadrowski Turbine wheel.
US906400A (en) * 1905-12-15 1908-12-08 Sebastian Ziani De Ferranti Process for attaching turbine-blades to their carrying elements.
US1610010A (en) * 1922-12-06 1926-12-07 Westinghouse Electric & Mfg Co Rotor construction
US1708044A (en) * 1923-09-12 1929-04-09 Westinghouse Electric & Mfg Co Labyrinth-gland packing
GB377289A (en) * 1931-04-24 1932-07-25 Richard William Bailey Improvements in and relating to turbine discs, fly wheels and like rotary parts
US2333053A (en) * 1940-01-05 1943-10-26 Gen Electric High temperature elastic fluid turbine
GB585350A (en) * 1943-07-08 1947-02-05 Cyril Armer Improvements in or relating to the cooling of turbine wheels and blades
GB643259A (en) * 1947-04-10 1950-09-15 Brush Electrical Eng Improvements in or relating to turbine or the like wheels
US2623727A (en) * 1945-04-27 1952-12-30 Power Jets Res & Dev Ltd Rotor structure for turbines and compressors

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE563092C (de) * 1929-03-22 1932-11-01 Georg Jendrassik Dipl Ing Waermeschutz fuer ein radial durchstroemtes Gasturbinenrad
DE593837C (de) * 1931-04-19 1934-03-06 E H Hans Holzwarth Dr Ing Erosionsfeste Schaufel fuer mit staubfoermigen Brennstoffen betriebene Brennkraftturbinen
DE716062C (de) * 1939-07-22 1942-01-12 Holzwarth Gasturbinen G M B H Traeger fuer die Leit- bzw. Umkehrschaufeln hochbeanspruckter Kreiselmaschinen, insbesondere von Verpuffungsbrennkraftturbinen
DE800800C (de) * 1948-10-02 1950-12-07 Maschf Augsburg Nuernberg Ag Turbinenlaeufer fuer hohe Temperaturen

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US702461A (en) * 1901-12-19 1902-06-17 Johannes Nadrowski Turbine wheel.
US906400A (en) * 1905-12-15 1908-12-08 Sebastian Ziani De Ferranti Process for attaching turbine-blades to their carrying elements.
US1610010A (en) * 1922-12-06 1926-12-07 Westinghouse Electric & Mfg Co Rotor construction
US1708044A (en) * 1923-09-12 1929-04-09 Westinghouse Electric & Mfg Co Labyrinth-gland packing
GB377289A (en) * 1931-04-24 1932-07-25 Richard William Bailey Improvements in and relating to turbine discs, fly wheels and like rotary parts
US2333053A (en) * 1940-01-05 1943-10-26 Gen Electric High temperature elastic fluid turbine
GB585350A (en) * 1943-07-08 1947-02-05 Cyril Armer Improvements in or relating to the cooling of turbine wheels and blades
US2623727A (en) * 1945-04-27 1952-12-30 Power Jets Res & Dev Ltd Rotor structure for turbines and compressors
GB643259A (en) * 1947-04-10 1950-09-15 Brush Electrical Eng Improvements in or relating to turbine or the like wheels

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3055633A (en) * 1957-04-19 1962-09-25 Pouit Robert Hot gas turbines
US2996280A (en) * 1959-04-07 1961-08-15 Iii John A Wilson Heat shield
US5507620A (en) * 1993-07-17 1996-04-16 Abb Management Ag Gas turbine with cooled rotor
US20030101730A1 (en) * 2001-12-05 2003-06-05 Stefan Hein Vortex reducer in the high-pressure compressor of a gas turbine
US7159402B2 (en) * 2001-12-05 2007-01-09 Rolls-Royce Deutschland Ltd & Co Kg Vortex reducer in the high-pressure compressor of a gas turbine

Also Published As

Publication number Publication date
DE943328C (de) 1956-05-17
CH295196A (de) 1953-12-15

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