EP0353447A1 - Schlitze für den axialen Einschub von Turbinenschaufeln in eine Rotorscheibe - Google Patents

Schlitze für den axialen Einschub von Turbinenschaufeln in eine Rotorscheibe Download PDF

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Publication number
EP0353447A1
EP0353447A1 EP89111415A EP89111415A EP0353447A1 EP 0353447 A1 EP0353447 A1 EP 0353447A1 EP 89111415 A EP89111415 A EP 89111415A EP 89111415 A EP89111415 A EP 89111415A EP 0353447 A1 EP0353447 A1 EP 0353447A1
Authority
EP
European Patent Office
Prior art keywords
rotor
mounting groove
mounting
lug
portions
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.)
Withdrawn
Application number
EP89111415A
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English (en)
French (fr)
Inventor
Roger Walter Heinig
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.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Publication of EP0353447A1 publication Critical patent/EP0353447A1/de
Withdrawn legal-status Critical Current

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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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/34—Non-positive-displacement machines or engines, e.g. steam turbines characterised by non-bladed rotor, e.g. with drilled holes
    • 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • This invention relates generally to steam turbines and, more particularly, to side-entry grooves arrangements for mounting turbine blades in the grooves.
  • a steam turbine can include a combination of low pressure, intermediate pressure, and/or high pressure steam turbine elements which are coupled together to provide a single power output.
  • Each steam turbine includes a rotor having a plurality of rotating blades mounted thereon in rows.
  • the blades of a given row are identical to each other.
  • the rotating blades of a row extend radially outwardly from an outer surface of the rotor, with the rows being spaced apart.
  • the rotating blades of one row differ in shape from those of the other rows; most noticeably, the rotating blades of each row, or stage, vary in length depending on position along the rotor.
  • Each rotating blade regardless of row, has a foil portion extending radially outwardly from the rotor and a base portion for mounting the blade to the rotor.
  • the base portion includes a root which is fitted into a mounting groove provided for each blade of a row, and a platform integrally formed at the proximal end of the foil portion.
  • the foil portion has a tip at the distal end and may have a twist profile from the proximal end to the distal end, or may be parallel-sided. It is common to provide shrouds at the tips as separately added or integrally formed components.
  • a stationary cylinder is coaxially supported around the rotor and has a plurality of stationary blades mounted on an inner surface thereof.
  • the stationary blades are arranged in rows which, when the cylinder is assembled with the rotor, alternate with rows of rotating blades.
  • the stationary blades of one row are shaped differently from those of the other rows, although all stationary blades have a foil portion.
  • the tips of the foil portions may be shrouded together by a series of shrouds.
  • Some stationary blades have a base portion which includes a root and a platform. Others have the foil portion welded directly into blade rings, with no root or platform.
  • each stationary blade may be provided with a side notch which, when the root is fitted into the groove, aligns with the annular recess.
  • the side notch and the annular recess together define a space which is common to both the cylinder and the root. When the space is filled with caulking material, the cylinder and root become interconnected.
  • Rotor blade grooves provided in the rotor for mounting the rotor blades are usually geometrically more complex than the mounting grooves provided for stationary blades. Moreover, the roots of the rotating blades and the rotor are subjected to substantially greater stresses than corresponding roots of stationary blades.
  • a side-entry groove arrangement includes, for a given row, a series of equidistantly spaced apart side-entry grooves, each side-­entry groove of the series being provided for each rotor blade of the row.
  • the side-entry grooves are usually equidistantly spaced, sometimes spacing is varied to facilitate assembly of a closing blade.
  • a typical side-entry groove starts at the outer surface of the rotor as an opening which tapers inwardly towards a bottom of the groove.
  • a series of undulations are provided between the opening and the bottom of the groove symmetrically on opposite side walls of the groove.
  • a typical root of a corresponding turbine rotor blade has a shape which substantially conforms to that of the groove.
  • the undulations provide a series of interlocking steps.
  • the undulating side walls also make it impossible to insert the root into the groove radially relative to the rotor.
  • a root contour tolerance envelope for contact surfaces typically varies along the contour of the root from 0.0025 to 0.0127 mm.
  • a groove contour tolerance envelope for contact surfaces typically varies along the profile of the groove from about 0.015 to 0.02 mm. Basically, a precise fitting between the root and the groove is required such that the maximum clearance between the root and groove is extremely small, on the order of about 0.4 mm.
  • cooling slots have been formed by cutting the groove deeper.
  • the deeper cut groove is cut during the original manufacture of the turbine rotor; it is an essential part of the design.
  • the practice of cutting a deeper groove has been used specifically to the first one or two rows of the inter­mediate pressure section of a fossil-fueled turbine.
  • the present invention resides in a rotor assembly for a steam turbine, wherein the rotor has a plurality of rotor blade mounting portions formed circumferentially thereon, a plurality of side-­entry mounting grooves formed in each of the plurality of mounting portions equidistantly spaced on the circum­ference of the rotor, and being substantially axially oriented with respect to the rotor, each mounting groove having two symmetrically contoured opposite side walls and a bottom wall; with at least one row of rotor blades mounted to the rotor at one of the plurality of mounting portions in the plurality of mounting grooves, the rotor blades within each such row being substantially identical to each other, and each blade having a root portion, a platform portion, and a foil portion; each root portion being substantially conforming in shape to each cor­responding mounting groove; characterized in that cooling passages are disposed on opposite sides of said bottom-­most lug portions between the adjacent surface areas of the mounting groove and the lug portions
  • the two cooling passages or slots may be formed by cutting into opposite side walls of the mounting groove, or they may be formed by cutting opposite sides of the bottom-most lug portion of the root portion diagonally from each side thereof to the bottom thereof.
  • FIG. 1 partially illustrates a portion of a steam turbine 10 which includes a rotor 12 (partially shown), and a stationary cylinder 14 (partially shown) which completely surrounds the rotor 12.
  • a plurality of rotor blades 16, 18, 20, 22, 24, and 26 are mounted in rows on the rotor 12. Each of the rotor blades is mounted in a different row. Each row is disposed circumferential­ly on the rotor 12. Each rotor blade extends radially outwardly from an outer surface of the rotor 12.
  • Each of the six rotor blades illustrated in FIG. 1 is disposed in a separate row.
  • the cylinder 14 supports a plurality of stationary blades 28, 30, 32, 34, 36, and 38 which also are disposed in a plurality of corresponding rows. As shown in FIG. 1, the stationary blades alternate with the rotor blades.
  • a housing 40 (partially shown) envelops both the cylinder 14 and the rotor 12 and is provided with steam seals 42 which allow the rotor 12 to rotate without letting steam escape between the rotor 12 and the housing 40. Steam seals 42 are also provided between the tips of the rotor blades and the cylinder, and between the tips of the stationary blades and the rotor.
  • the rotor 12 is shown in greater detail with the blades 16-26 and all other structure removed.
  • the rotor 12 is provided with a plurality of rotor blade mounting portions 44, 46, 48, 50, 52, and 54, each extending circumferentially on the rotor 12.
  • FIG. 3 illustrates an enlarged cross-sectional view of a portion of the mounting portion 54 shown in FIG. 2.
  • the mounting portion 54 is provided with a plurality of side-entry mounting grooves 56, 58, and 60 which extend inwardly from an outer surface 62 of the mounting portion 54.
  • Each mounting groove has a bottom wall 64 and opposite side walls 66 and 68.
  • the opposite side walls 66 and 68 are symmetrically undulating and taper inwardly.
  • a bottom space 70 is defined by the bottom wall 64 and a pair of opposite side lobes 72. Additional pairs of lobes 74 and 76 define increasingly larger spaces as viewed upwardly from the bottom space 70.
  • FIG. 4 shows the mounting grooves 56, 58, and 60 from a top view, and further illustrates grooves 78 which help facilitate securing the rotor blades within respec­tive mounting grooves.
  • FIG. 5 illustrates a typical rotor blade 26 which includes a root 80, a platform 82, a foil portion 84 and a shrouded tip portion 86.
  • the shroud is integrally formed with the blade, but may be separately formed. In the latter case, the shroud may be riveted onto the blade tip by deforming a projection from the blade tip, known as a tenon.
  • a bottom of the platform 82 is substantially flush with the top of the mounting portion 54.
  • a groove 88 of the platform 82 is in alignment with the corresponding groove 78 of the mounting groove 56 (not shown).
  • Each root 80 has a series of necks 90, 92 and 94 which increase in width from the lower-most neck 90 to the upper-most neck 94. These necks define lugs 96, 98, and 100, which also increase in width from the bottom-most lug 96 to the upper-most lug 100.
  • Cooling slots 102 and 104 are provided on opposite sides of the lug 96, and are formed by cutting into the side walls 66, 68, respectively, of the mounting groove 56 at the bottom space 70.
  • the cooling slots 102 and 104 are defined by a space between cut-away surfaces 103 and 105 of the mounting groove 56 and sloping side walls 106 and 108 of the bottom-most lug 96.
  • the opposite side cooling slots 102 and 104 avoid increasing the rotor nominal tangential stress and reduce the rotor tangential stress concentration.
  • FIG. 8 A variation of the FIG. 7 embodiment is illustrated in FIG. 8, wherein the bottom-most lug 96 has its bottom corners cut-away to form oppositely angled surfaces 110 and 112, which are symmetrically disposed about a centerline 114 of the root 80.
  • Broken lines 116 and 118 represent either the former outline of the root 80 before cutting, or the current profile of the bottom space of the mounting groove.
  • Opposite side cooling slots 120 and 122 are defined by the spaces between the angled surfaces 110 and 112 and a portion of the mounting groove bottom wall and side walls.
  • stress patterns were modeled by computer to determine the effect of the opposite side cooling slots 120, 122. Stress was calculated based on centrifugal loading, with all lugs 96-­100 in perfect contact with corresponding areas of the mounting groove 56. As a result of the computer modeling, it was determined that peak elastic stress at the bottom neck of the root (numeral 90 in FIG. 5) increased by only 8%. The lower amount of stress is accompanied by a greater area of heat transfer and a greater uniformity of flow around the circumference of the rotor, compared to the conventional approach of deepening the groove. Moreover, standard root cutters could be used instead of a special tool which would be required to cut deeper, special grooves.
  • broken line 124 represents a portion of the bottom-most lug portion 96 that has been cut-away to form a cooling slot 126.
  • the cooling slot 126 is defined by the space between bottom wall 128 of the truncated lug portion 96 and a bottom wall of the mounting groove, which may also be represented by the broken line 124.
  • the portion of the mounting groove which helps define the cooling slot 126 includes portions of the opposite side walls of the mounting groove as indicated by the curved end portions of the broken line 124.
  • FIG. 9 was also tested by computer modeling for stress induced by centrifugal loading. A calculated 14% increase in the peak elastic stress at the bottom neck resulted.
  • the advantage to the embodiment of FIG. 9 is that the groove can be cut with standard cutters.
  • the cooling area is approximately 32 mm2 in cross section.
  • FIG. 8 has proven to have stress minimizing ability over the embodiments of FIGS. 7 and 9, all are deemed improve­ments over the known technique of enlarging the bottom of the mounting groove.
EP89111415A 1988-07-29 1989-06-22 Schlitze für den axialen Einschub von Turbinenschaufeln in eine Rotorscheibe Withdrawn EP0353447A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US22626388A 1988-07-29 1988-07-29
US226263 2002-08-23

Publications (1)

Publication Number Publication Date
EP0353447A1 true EP0353447A1 (de) 1990-02-07

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ID=22848205

Family Applications (1)

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EP89111415A Withdrawn EP0353447A1 (de) 1988-07-29 1989-06-22 Schlitze für den axialen Einschub von Turbinenschaufeln in eine Rotorscheibe

Country Status (4)

Country Link
EP (1) EP0353447A1 (de)
JP (1) JPH0270904A (de)
KR (1) KR910003237A (de)
CN (1) CN1039873A (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0649975A1 (de) * 1993-10-26 1995-04-26 United Technologies Corporation Kühlluftmengenregelung bei Turbinenschaufeln
EP0859127A1 (de) * 1997-02-13 1998-08-19 BMW Rolls-Royce GmbH Kühlluftführung in einer Turbinen-Laufradscheibe
FR3140649A1 (fr) * 2022-10-07 2024-04-12 Safran Aircraft Engines Disque pour une turbine de turbomachine d’aeronef

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5322664B2 (ja) * 2009-01-14 2013-10-23 株式会社東芝 蒸気タービン及びその冷却方法
EP2428642A1 (de) * 2010-09-08 2012-03-14 Siemens Aktiengesellschaft Rotor für eine Dampfturbine mit zur Rotorachse geneigten Umfangsausnehmungen
CN117307254B (zh) * 2023-11-28 2024-01-23 成都中科翼能科技有限公司 一种燃气轮机的涡轮转子结构

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB579316A (en) * 1941-05-07 1946-07-31 Hayne Constant Improvements in gas turbines, axial flow or turbine type gas compressors and the like machines
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus
DE1076446B (de) * 1957-10-25 1960-02-25 Siemens Ag Einrichtung zur Schaufelkuehlung bei Gasturbinen
US3045968A (en) * 1959-12-10 1962-07-24 Gen Motors Corp Fir tree blade mount
FR1526683A (fr) * 1967-06-12 1968-05-24 United Aircraft Corp Disque de turbine refroidi
DE1928184A1 (de) * 1968-06-24 1970-01-08 Westinghouse Electric Corp Befestigungs- und Kuehlanordnung fuer Laufschaufelkraenze von Turbomaschine,vorzugsweise Gasturbinen
GB1183835A (en) * 1967-08-31 1970-03-11 Prvni Brnenska Strojirna Zd Y Improvements in or relating to the Regulation of Cooling-Air Flow in Gas Turbines.
DE1953711A1 (de) * 1968-10-28 1970-04-30 Elin Union Ag Sicherung fuer in profilierten axialen Nuten eines Turbinenrotors gehaltene Laufschaufeln gegen eine Axialverschiebung
CH495496A (de) * 1969-02-26 1970-08-31 Bbc Sulzer Turbomaschinen Turbomaschine mit gekühltem Rotor
GB1211188A (en) * 1968-08-30 1970-11-04 Gen Motors Corp Gas turbine engines

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2057573A (en) * 1979-08-30 1981-04-01 Rolls Royce Turbine rotor assembly
JPS5832905A (ja) * 1981-08-21 1983-02-26 Agency Of Ind Science & Technol 翼冷却装置
JPS59113206A (ja) * 1982-12-20 1984-06-29 Hitachi Ltd タ−ボ機械のブレ−ド取付構造
JPS61205302A (ja) * 1985-03-06 1986-09-11 Mitsubishi Heavy Ind Ltd タ−ビン動翼の軸方向翼止装置

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB579316A (en) * 1941-05-07 1946-07-31 Hayne Constant Improvements in gas turbines, axial flow or turbine type gas compressors and the like machines
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus
DE1076446B (de) * 1957-10-25 1960-02-25 Siemens Ag Einrichtung zur Schaufelkuehlung bei Gasturbinen
US3045968A (en) * 1959-12-10 1962-07-24 Gen Motors Corp Fir tree blade mount
FR1526683A (fr) * 1967-06-12 1968-05-24 United Aircraft Corp Disque de turbine refroidi
GB1183835A (en) * 1967-08-31 1970-03-11 Prvni Brnenska Strojirna Zd Y Improvements in or relating to the Regulation of Cooling-Air Flow in Gas Turbines.
DE1928184A1 (de) * 1968-06-24 1970-01-08 Westinghouse Electric Corp Befestigungs- und Kuehlanordnung fuer Laufschaufelkraenze von Turbomaschine,vorzugsweise Gasturbinen
GB1211188A (en) * 1968-08-30 1970-11-04 Gen Motors Corp Gas turbine engines
DE1953711A1 (de) * 1968-10-28 1970-04-30 Elin Union Ag Sicherung fuer in profilierten axialen Nuten eines Turbinenrotors gehaltene Laufschaufeln gegen eine Axialverschiebung
CH495496A (de) * 1969-02-26 1970-08-31 Bbc Sulzer Turbomaschinen Turbomaschine mit gekühltem Rotor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0649975A1 (de) * 1993-10-26 1995-04-26 United Technologies Corporation Kühlluftmengenregelung bei Turbinenschaufeln
EP0859127A1 (de) * 1997-02-13 1998-08-19 BMW Rolls-Royce GmbH Kühlluftführung in einer Turbinen-Laufradscheibe
US5957660A (en) * 1997-02-13 1999-09-28 Bmw Rolls-Royce Gmbh Turbine rotor disk
FR3140649A1 (fr) * 2022-10-07 2024-04-12 Safran Aircraft Engines Disque pour une turbine de turbomachine d’aeronef

Also Published As

Publication number Publication date
JPH0270904A (ja) 1990-03-09
CN1039873A (zh) 1990-02-21
KR910003237A (ko) 1991-02-27

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