EP1882813A2 - Disque de montage pour des aubes de turbine ou compresseur - Google Patents

Disque de montage pour des aubes de turbine ou compresseur Download PDF

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Publication number
EP1882813A2
EP1882813A2 EP07252734A EP07252734A EP1882813A2 EP 1882813 A2 EP1882813 A2 EP 1882813A2 EP 07252734 A EP07252734 A EP 07252734A EP 07252734 A EP07252734 A EP 07252734A EP 1882813 A2 EP1882813 A2 EP 1882813A2
Authority
EP
European Patent Office
Prior art keywords
disc
deviation
cob
mounting
radial plane
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Withdrawn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
EP07252734A
Other languages
German (de)
English (en)
Other versions
EP1882813A3 (fr
Inventor
Philip Scope
Nicholas Bayley
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP1882813A2 publication Critical patent/EP1882813A2/fr
Publication of EP1882813A3 publication Critical patent/EP1882813A3/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex

Definitions

  • the present invention relates to mounting discs and more particularly to a mounting disc utilised to secure rotating blades in compressor or turbine stages of a gas turbine engine.
  • a gas turbine engine is generally indicated at 10 and comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, a combustor 15, a turbine arrangement comprising a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18, and an exhaust nozzle 19.
  • the gas turbine engine 10 operates in a conventional manner so that air entering the intake 11 is accelerated by the fan 12 which produce two air flows: a first air flow into the intermediate pressure compressor 13 and a second air flow which provides propulsive thrust.
  • the intermediate pressure compressor compresses the air flow directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • the compressed air exhausted from the high pressure compressor 14 is directed into the combustor 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 16, 17 and 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low pressure turbines 16, 17 and 18 respectively drive the high and intermediate pressure compressors 14 and 13 and the fan 12 by suitable interconnecting shafts.
  • a gas turbine engine incorporates a number of compressor and turbine stages.
  • the blades for those compressor and turbine stages are secured upon mounting discs such that the blades can rotate as appropriate.
  • the mounting discs are secured to the rotating shaft through a disc cob.
  • relatively high temperatures are generated within a gas turbine engine such that the engine thermo dynamic cycle dictates to a significant extent the disc cob size.
  • the weight efficient solution to meet an over speed requirement is to provide a flat cob end for the mounting disc. Rotational speed and mass dictate size whilst thermal gradients worsen stressing for large disc sizes.
  • biaxial stress relates to both centrifugal stress (hoop) and axial stress within the cob end. Furthermore, accumulation of significant axial compressive stress in conjunction with high hoop stress results in a considerable fatigue life reduction when compared to a uniaxial stress field of the same magnitude.
  • Such a combination of hoop and axial stress is generally combined into a single stress measure called Von-Mises stress and it is accepted that the higher the Von-Mises stress, the sooner a fatigue crack will be initiated resulting in a lower fatigue life.
  • a disc for mounting rotating components characterised in that the bore end has an outward deviation from a flat perpendicular aspect relative to the radial plane.
  • the deviation is outward.
  • the deviation is a convex curve.
  • the convex curve has a consistent convex radius. Potentially, the convex radius has a maximum radius equivalent to half of the axial width of the disc across the radial plane.
  • the convex curve is a smooth curve. Potentially, the convex curve is conic. Potentially, the convex curve is semi circular.
  • the deviation comprises a trapezoidal shape for the cob or bore end.
  • the trapezoidal shape has a side projection relative to the radial plane having an angle in the range 5 - 45°.
  • the deviation is triangular.
  • an apex for the triangular deviation is rounded.
  • the cob or bore end has a stepped portion to achieve a desired weight distribution in the disc.
  • a ratio of the depth of the deviation divided by width of the mounting disc across from the flat perpendicular to the radial plane is in the range 0.03 to 0.5.
  • the shape and extent of deviation provided is subject to material and rotational speed determined to substantially provide zero compression axial stress differential across the mounting end.
  • Fig. 2 illustrates a typical flat or plain end mounting disc configuration. It will be appreciated that only one side of the mounting discs is illustrated with an annular disc secured upon a rotating shaft.
  • the mounting disc 120 has three major portions namely, a bore or cob end 121, a diaphragm portion 122 and a rim portion 123.
  • the bore end 121 essentially allow the mounting disc 120 to be secured to a shaft.
  • mounting discs 120 are utilised with respect to turbine blades and compressor blades in a gas turbine engine. Particularly with respect to high pressure turbine blades it will be understood that increasing thrust increases the level of hot gasses adjacent to the mounting disc and therefore heating of the cob area 121.
  • thermal inertia ensures that peripheral surface portions of the cob end 121 heat up much quicker than central parts of the cob end 121 resulting in a temperature differential of a few hundred degrees centigrade across the cob end 21.
  • the stresses on the cob or bore end are a combination of axial stress due to rotation of the mounting discs and associated blades as well as circumferential. These stresses are combined as Von-Mises stresses.
  • FIG. 124 schematically illustrates a typical axial stress band in a flat or plane face mounting end 121.
  • these stresses can result in premature failure or a design limitation on shaft speed or both.
  • an objective is to optimise in terms of shape the mounting end 121 to minimise or control Von-Mises stress.
  • it is the net effect in reducing Von-Mises stress that is desirable in order to achieve an increased life at the bore surface.
  • selecting a profile which significantly reduces the level of compressive axial stresses although slightly increasing the circumferential stress would be acceptable in terms of achieving a net reduction in Von-Mises stresses or vice versa.
  • a further advantage is with regard to separating the location of peak hoop stress and peak axial stress within the disk 120. As indicated, by achieving a net reduction in Von-Mises stress, a greater disc fatigue life and potentially higher shaft speeds will be possible.
  • aspects of the present invention relate to providing a deviation from a flat surface as depicted in Fig 2.
  • by providing a convexed or other outward deviation from a flat perpendicular aspect relative to a radial plane will allow material to expand more readily reducing barriers to expansion and therefore stresses.
  • Fig. 3 illustrates a trapezoidal cob or bore end 31 in a disc 30. It has been found by re-distributing the material in the cob end 31, as indicated above, there is an overall increase in allowability with respect to expansion such that stress distribution shown by broken line 34 results in a peak hoop stress at an area 35 and peak axial stress at an area 36. It has been found that the axial compression stress is lowered whilst there is an increase in the hoop stress but overall the net result is a Von-Mises stress level which is lower and therefore a net improvement in operational performance. By creating the deviation from a flat perpendicular aspect shown by the plane X rearwardly the benefits with respect to reduction of Von-Mises stresses is achieved.
  • the disc 31 has a general radial plane 37 through its centre line and the cob or mounting end 31 extends either side of this radial plane 37. In such circumstances, it is the deviation in a face 39 of the cob or mounting end 31 along the radial plane 37 which is determinant as to the stress variation. It can be seen that this deviation has a depth depicted between arrowheads 38 along the radial plane 37 and, as indicated, generally takes a trapezoidal shape in the first embodiment depicted in Fig. 3.
  • the angle 33 at the sides may be in the range of 5 - 45° dependent upon requirements.
  • Fig. 4 illustrates a typical convex end face 49 to a cob or bore 41 of a disc 40.
  • the disc 40 has a radial plane 47.
  • the face 49 deviates by a depth 48 with a smooth convex curve. In such circumstances, again by shaping of the face expansion is more readily allowed so reducing Von-Mises stress and therefore operational effectiveness of the disc 40.
  • Fig. 5 illustrates a third embodiment of a disc in accordance with aspects of the present invention.
  • the disc 50 has a cob or mounting end 51 with an end face 59 which deviates to the depth 58 for a continual flat perpendicular aspect X - X relative to a radial plane 57 for the disc 50.
  • a face 59 substantially reflects a triangle which again through shaping allows easier expansion and therefore reduction in Von-Mises stresses within the end 51 resulting in a longer operational life and/or potentially higher rotational speeds for the disc 50.
  • the triangular nature of the end 51 is exaggerated for illustration purposes.
  • a maximum amount of material in the cob end should be towards the radial plane of the disc.
  • a fully semi circular end face 69 would be ideal in a disc 60 in order to provide the desired material distribution.
  • the end face 69 would be ideal in a disc 60 in order to provide the desired material distribution.
  • the end face 69 extends away from notional flat perpendicular plane to a radial plane 67 of the disc 60.
  • aspects of the present invention provide through the deviation to the face for the bore or cob end potential for adjusting the Von-Mises stress effects.
  • the particular degree and shape of deviation in the cob or mounting end will depend upon operational requirements in terms of material available, acceptability of weight penalties and desired or expected rotational speeds.
  • the deviation is a convexed face (Fig. 4) it is expected that the maximum radius of the curvature will be half the axial width of the bore, that is to say the width of the disc extending either side of the radial plane of that disc.
  • the side angles will be in the range 5 - 45° leading to a flat bottom surface of narrower width.
  • the cob end may incorporate a triangular end face with an apex end of that triangle rounded.
  • the cob end may incorporate, as indicated, a smooth convex surface and that this smooth surface may be conic in section.
  • the depth of deviation (38 in Fig. 3, 48 in Fig. 4, 58 in Fig. 5) will be in the ratio whereby the deviation depth divided by the width of the cob or mounting end relative to the radial plane will be in the range 0.03 to 0.5.
  • deviation depth relative to width will be chosen to reduce maximum compressive axial stress differential across the disc bore in comparison with a disc bore with no deviation depth, that is to say flat or plain.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP07252734.4A 2006-07-28 2007-07-07 Disque de montage pour des aubes de turbine ou compresseur Withdrawn EP1882813A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB0614972.8A GB0614972D0 (en) 2006-07-28 2006-07-28 A mounting disc

Publications (2)

Publication Number Publication Date
EP1882813A2 true EP1882813A2 (fr) 2008-01-30
EP1882813A3 EP1882813A3 (fr) 2013-09-04

Family

ID=37006299

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07252734.4A Withdrawn EP1882813A3 (fr) 2006-07-28 2007-07-07 Disque de montage pour des aubes de turbine ou compresseur

Country Status (3)

Country Link
US (1) US20080025843A1 (fr)
EP (1) EP1882813A3 (fr)
GB (1) GB0614972D0 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3633144A1 (fr) * 2018-10-04 2020-04-08 Rolls-Royce plc Disque de compresseur
US11021957B2 (en) 2017-05-26 2021-06-01 Siemens Energy Global GmbH & Co. KG Gas turbine engine rotor disc retention assembly

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10544677B2 (en) 2017-09-01 2020-01-28 United Technologies Corporation Turbine disk
US10633985B2 (en) * 2012-06-25 2020-04-28 General Electric Company System having blade segment with curved mounting geometry
US10024170B1 (en) * 2016-06-23 2018-07-17 Florida Turbine Technologies, Inc. Integrally bladed rotor with bore entry cooling holes
US10724374B2 (en) 2017-09-01 2020-07-28 Raytheon Technologies Corporation Turbine disk
US10550702B2 (en) 2017-09-01 2020-02-04 United Technologies Corporation Turbine disk
US10472968B2 (en) 2017-09-01 2019-11-12 United Technologies Corporation Turbine disk
US10641110B2 (en) 2017-09-01 2020-05-05 United Technologies Corporation Turbine disk

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0272966A1 (fr) * 1986-12-03 1988-06-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Système de liaison des disques pour un rotor de turbomachine
US5860789A (en) * 1996-03-19 1999-01-19 Hitachi, Ltd. Gas turbine rotor
EP1503036A2 (fr) * 2003-07-28 2005-02-02 United Technologies Corporation Contour du trou de moyeu dans un disque de turbine
EP1512834A2 (fr) * 2003-09-04 2005-03-09 General Electric Company Déflecteur d'air de refroidissement pour cavité tournante de turbine à gaz
EP1801349A1 (fr) * 2005-12-20 2007-06-27 General Electric Company Moyeu de roue de turbine haute pression avec une contrainte axiale réduite et procédé
EP1801347A2 (fr) * 2005-12-20 2007-06-27 General Electric Company Moyeu de papillon de turbine haute pression avec une surface de moyeu incurvée et procédé

Family Cites Families (8)

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Publication number Priority date Publication date Assignee Title
DE3708507A1 (de) * 1987-03-16 1988-09-29 Siemens Ag Verfahren zur herstellung von turbinenradscheiben mit oertlichen hohen druckeigenspannungen in der nabenbohrung
US5215440A (en) * 1991-10-30 1993-06-01 General Electric Company Interstage thermal shield with asymmetric bore
US5320488A (en) * 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
FR2712029B1 (fr) * 1993-11-03 1995-12-08 Snecma Turbomachine pourvue d'un moyen de réchauffage des disques de turbines aux montées en régime.
CA2333808C (fr) * 2000-02-01 2011-01-04 Metaullics Systems Co., L.P. Pompe pour matieres en fusion avec solides en suspension
DE102004016244B4 (de) * 2004-04-02 2007-08-23 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
EP1614857A1 (fr) * 2004-07-05 2006-01-11 Siemens Aktiengesellschaft Turbomachine ayant un rotor composé d'au moins un disque percé
US7470115B2 (en) * 2004-07-13 2008-12-30 Honeywell International Inc. Outer diameter nut piloting for improved rotor balance

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0272966A1 (fr) * 1986-12-03 1988-06-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Système de liaison des disques pour un rotor de turbomachine
US5860789A (en) * 1996-03-19 1999-01-19 Hitachi, Ltd. Gas turbine rotor
EP1503036A2 (fr) * 2003-07-28 2005-02-02 United Technologies Corporation Contour du trou de moyeu dans un disque de turbine
EP1512834A2 (fr) * 2003-09-04 2005-03-09 General Electric Company Déflecteur d'air de refroidissement pour cavité tournante de turbine à gaz
EP1801349A1 (fr) * 2005-12-20 2007-06-27 General Electric Company Moyeu de roue de turbine haute pression avec une contrainte axiale réduite et procédé
EP1801347A2 (fr) * 2005-12-20 2007-06-27 General Electric Company Moyeu de papillon de turbine haute pression avec une surface de moyeu incurvée et procédé

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DEM'YANUSHKO I V ET AL: "OPTIMAL DESIGN OF ROTATING DISKS", RUSSIAN ENGINEERING RESEARCH, ALLERTON PRESS, NEW YORK, NY, US, vol. 16, no. 7, 1 January 1996 (1996-01-01), pages 7-13, XP000699743, ISSN: 1068-798X *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11021957B2 (en) 2017-05-26 2021-06-01 Siemens Energy Global GmbH & Co. KG Gas turbine engine rotor disc retention assembly
EP3633144A1 (fr) * 2018-10-04 2020-04-08 Rolls-Royce plc Disque de compresseur

Also Published As

Publication number Publication date
US20080025843A1 (en) 2008-01-31
GB0614972D0 (en) 2006-09-06
EP1882813A3 (fr) 2013-09-04

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