US3817657A - Integral turbine wheel with axial through-openings at the outer rim and with controlled rim cracks - Google Patents

Integral turbine wheel with axial through-openings at the outer rim and with controlled rim cracks Download PDF

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Publication number
US3817657A
US3817657A US00304660A US30466072A US3817657A US 3817657 A US3817657 A US 3817657A US 00304660 A US00304660 A US 00304660A US 30466072 A US30466072 A US 30466072A US 3817657 A US3817657 A US 3817657A
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United States
Prior art keywords
turbine wheel
wheel according
apertures
section
pipe means
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Expired - Lifetime
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US00304660A
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English (en)
Inventor
A Hueber
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.)
MTU Aero Engines AG
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MTU Motoren und Turbinen Union Muenchen GmbH
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    • 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
    • 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
    • F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage

Definitions

  • the present invention relates to a turbine wheel in which the rim and blades are made of one piece, which is provided at the outer rim portion with intended-or predetermined breaking places for radial heat cracks at the ends of radial slots, andadditionally with throughopenings or apertures which extend through the rim portions in the axial direction and thereby prevent the heat cracks in their further radial-inwardly direction continuation or development;
  • a further aim of the present invention is to dampen the blade vibrations with suitable means.
  • the present invention essentially consists in that the throughopenings or apertures connect with each other the high pressure and low pressure side and in that the intended or predetermined breaking places are located between the slots and the through-openings. Consequently, whereas in the prior art, the bores were subsequently closed, they remain open in the solution according to the present invention.
  • the essentially axially extending through-openings or apertures arranged according to the present invention combine in an advantageous manner the intensive internal cooling of the turbine wheel-outer rim with the interception or stoppage of the controlled rim cracks whose location they additionally determine in conjunction with the radial slots. As a result thereof, they enable higher process or operating temperatures and reduce the danger of wheel breakages or fractures. Therebeyond, the rim cracks contribute toward the improvement of the temperature-altemate stress strength or temperature fatigue strength and to the damping of blade vibrations. Additionally, the expenditures required in the prior art wheels for sealing off the through-openings are saved by the connection of the high pressure side and low pressure side.
  • the axial through-openings are constructed prismshaped in a particularly appropriate manner. They extend at slight distances in parallel underneath the radial slots whereby the narrow remaining web represents the intended or predetermined breaking place.
  • Small tubular members or pipes are inserted into the throughopenings whose internal cross section is closed at one place by a partition wall. Additionally, the small pipes are so dimensioned that a sufficient gap remains between the through-opening andthe small pipes in order to permit the passageof a sufficient amount of cooling air.
  • the through-openings or apertures can be hollowed out already during the casting or can be produced also subsequently byboring or electro-chemical or electro-erosive removal processes of conventional type. The slots can be produced. in a similar manner.
  • the through-openings and small pipes have a circular cross section.
  • the through-openings can be bored and the small pipes can be constructed as rod stock whereby the manufacturing costs are considerably decreased.
  • the throughopenings have an oval, possibly an eliptical profile whereby the major axis is disposed radially to the wheel axis.
  • This shape enables a better stress distribution in the transition between blade base and solid disk.
  • the manufacture takes place appropriately by casting, but may also take place by other processes, for example, by the erosion process of conventional type.
  • the inserted small pipes may have an oval or any other suitable base cross section.
  • the small pipes are profiled on the outside thereof and more particularly in such a manner that three or more webs run along the outer surface thereof which serve for the maintenance of the desired radial distance between the small tubular member and the bore.
  • the channels for the cooling air are located in the circumferential direction between the webs.
  • the cooling air is thereby guided very close along the surface to be cooled which makes possible a good cooling with economically metered cooling air.
  • the manufacture then takes place, for example, by milling or remaing out the cooling channels between the webs.
  • the webs can be readily formed-in, and also base cross sections deviating from the round or oval shape can be readily manufactured for optimizing the cooling air channel cross section.
  • the through-openings and small pipes may be so constructed that the webs serving for the maintenance of the radial gaps are not disposed at the pipes but at the inner contour of the through-openings.
  • the shape or form thereof plays no decisive role, at least the manufacture of the small pipes can thus be simplified.
  • one of the webs in each through-opening, is somewhat wider than the other webs and is so arranged that it is located at the place disposed farthest radially outwardly in relation to the turbine wheel axis, and more particularly at the place where the intended breaking place terminates in the through-opening.
  • the intended breaking places already assure a good shielding of the cooling channels against hot gases entering from the outside by reason of their small dimensions and also by reason of the labyrinth effect of their breaking surfaces, as compared to machined-in continuous slots, it is additionally achieved by the aforementioned measure that the small pipe thereby comes to lie at the termination of the rim cracks and thereby still better seals the same. It is thereby of no importance whether the web belongs to the outer contour or to the small pipe; however, in the former case, the web must be so wide that the crack extends therethrough radially.
  • the small pipes are provided at both ends with one tab or lug each, which after the insertion of the small pipes into the through-openings are bent up approximately in the radially outward direction and thereby come to lie in grooves provided therefor on the side of the rim.
  • the small tubular members are secured against axial displacement and possibly also against rotation.
  • These lugs or tabs like the already mentioned wider webs, are also arranged radially outwardly so that the abutment of the webs and therewith their fixation is assisted during the operation by the centrifugal forces.
  • the cooling is to be improved by turbulence enhancement in the cooling air channels.
  • the small pipes are provided with bores outside of the web areas through which the cooling air is blown out of the inside of the pipe directly against the bore walls (impingement cooling).
  • the partition wall may be displaced within the small pipe, if so desired, up to the end of the small pipe on the low pressure side.
  • FIG. 1 is a cross-sectional view of an intergral turbine wheel according to the present invention whereby the intended breaking place and through-opening are indicated only in dash line for purposes of simplification of the drawing;
  • FIG. 2 is a cross-sectional view through the turbine wheel of FIG. 1, taken along line II-II of FIG. 1;
  • FIG. 3 is a cross-sectional view, taken along line III- III of FIG. 2;
  • FIG. 4 is a cross-sectional view taken along the IV--IV of FIG. 1, unwound in the plane of the drawing;
  • FIG. 5 is a cross-sectional view, taken along line VV of FIG. 4, of a through-opening according to the present invention with inserted small pipes;
  • FIG. 6 is a partial elevational view of the end face of the through-opening and small pipe, taken in the direction of arrow VI in FIG. 5;
  • FIGS. 7-10 are cross-sectional views through four embodiments of through-openings with inserted pipes and with difierent configurations of the throughopenings;
  • FIG. 1 1 is a partial elevational view of a modified embodiment in accordance with the present invention representing an improved cooling system
  • FIG. 12 is a cross-sectional view taken along line XII- XII of FIG. 1, illustrating the through-opening and inserted pipe in accordance with the present invention.
  • the turbine wheel illustrated in cross section in FIG. 1 consists essentially of the disk 1, of the rim 2 and of the blades 3.
  • a through-opening or aperture 4 according to the present invention which is constructed in this embodiment as bore, an intended breaking place 5 and a radial slot 6 are illustrated in FIG. 1 only in dash lines for the sake of simplicity.
  • the inserted small tube or pipe was omitted for the sake of simplicity.
  • FIG. 2 taken along line Il-II of FIG. 1', which lies in the disk plane, illustrates two through-openings or apertures 7 with the associated intentional breaking places 5 and the radial slots 6.
  • the through-openings 7 do not extend parallel to the turbine axis, they appear oval in this figure.
  • Two narrow webs 9 and a wider web 10 are made in one piece with the small pipe 8.
  • the cooling channels 12 are thereby disposed-as viewed in the circumferential direction-between the webs.
  • FIGS. 3 and 4 The common direction of the radial slots 6 (according to the cross section III-III of FIG. 2) and of the through-openings 7 (cross section IV-IV in FIG. 2) which deviates from the direction parallel to the turbine axis, are illustrated in FIGS. 3 and 4. Additionally, the arrangement of one through-opening 7 each between two adjacent blade bases can be recognized in FIG. 3.
  • the inserted small tubular members or small pipes are provided with partition walls 11 as shown in FIG. 4.
  • a cross section according to line V-V of FIG. 4 illustrates in FIG. 5 the same small pipe with the lugs or tabs 13 for fixing the same in the installed position.
  • the end face of the small pipe equipped with a securing lug 13 is illustrated in FIG. 6 representing a partial elevational view taken in the direction of arrow VI of FIG. 5.
  • FIGS. 7, 8, 9 and 10 Four different embodiments for the throughopenings and small pipes are illustrated in FIGS. 7, 8, 9 and 10.
  • the plane of cross section in each case thereby is to be considered as extending along the line VII-VII of FIG. 5.
  • FIGS. 7 and 9 thereby illustrate through-openings 7 and 14 and small pipes 8 and 15 having a circular base shape whereas FIGS. 9 and 10 illustrate similar through-openings 18 and 22 and small pipes 19 and 23 having an eliptical base shape.
  • the webs 9, 10 and 20, 21 are made in one piece with the small pipes 8 and 19, respectively, whereas in the embodiments of FIGS. 8 and 10, the webs 16, 17 and 24, 25 are made in one piece with the rim, for example, by hollowing out during the casting.
  • a further improvement of the cooling results from the provision of the small pipes with bores 27 as can be seen in FIG. 11. These bores 27 extend through the pipe walls intermediate the webs 26 in the part of the pipes near the pressure side as delimited by the partition walls 28. In order not to restrict unnecessarily thereby the area of an intensive cooling, the partition wall 28 may be displaced somewhat toward the low pressure side.
  • a turbine wheel having rim means and blade means made in one piece, said rim means including an outer rim portion, comprising: radial slot means provided at said outer rim portion, means forming intentional breaking places for radial heat cracks provided at the ends of said radial slot means, aperture means disposed in said rim portion in a generally axially direction for preventing said radial heat cracks from continuing in a radially inward direction, said aperture means including means for communicating the high pressure side with the low pressure side of the turbine wheel, said intentional breaking places being disposed between said slot means and said aperture means.
  • aperture means include prism-shaped apertures and said communicating means includes small pipe means disposed in said apertures, said pipe means being provided with a partition wall means in the inner cross section thereof for substantially completely closing off said cross section, said small pipe means being disposed in said aperture means to permit a radial play therein.
  • a turbine wheel according to claim 3 wherein said apertures are of oval shape with the major axis of said oval shape being directed radially in relation to the turbine wheel axis, and wherein said small pipe means have an oval cross section.
  • a turbine wheel according to claim 4 wherein said apertures and said small pipe means have an eliptical cross section.
  • a turbine wheel according to claim 1 wherein the outer contour of said small pipe means is profiled and is provided with web means extending in the axial direction for the support of said small pipe means in the said aperture means, said web means forming therebetween channel means for the guidance of cooling air through the turbine wheel.
  • a turbine wheel according to claim 6, wherein said apertures are of oval shape with the major axis of said oval shape being directed radially in relation to the turbine wheel axis, and wherein said small pipe means have an oval cross section.
  • a turbine wheel according to claim 8 wherein said apertures and said small pipe means have an eliptical cross section.
  • said aperture means include prism-shaped apertures and said communicating means includes small pipe means disposed in said apertures, said pipe means being provided with a partition wall means in the inner cross section thereof for substantially completely closing off said cross section, said small pipe means being disposed in said aperture means to permit a radial play therein.
  • a turbine wheel according to claim 2 wherein said small pipe means is provided with a smooth outer contour, and wherein the inner walls of said apertures are, provided with substantially axially extending ribs forming webs.
  • a turbine wheel according to claim 11, wherein said apertures are of oval shape with the major axis of said oval shape being directed radially in relation to the turbine wheel axis, and wherein said small pipe means have an oval cross section.
  • a turbine wheel according to claim 2 a lug is provided at each end of said pipe means and the turbine wheel being provided with grooves engageable with said lugs, said grooves being disposed on the radially outwardly directed side of the apertures in relation to the turbine wheel axis.
  • a turbine wheel according to claim 2 wherein said pipe means are provided with web means and bores disposed between said web means, said bores being disposed on the side of said partition wall means near the pressure side of the turbine wheel.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00304660A 1971-11-08 1972-11-08 Integral turbine wheel with axial through-openings at the outer rim and with controlled rim cracks Expired - Lifetime US3817657A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2155344A DE2155344A1 (de) 1971-11-08 1971-11-08 Integrales turbinenrad mit offenen axialen durchbruechen am aeusseren kranz und kontrollierten kranzrissen

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US3817657A true US3817657A (en) 1974-06-18

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US00304660A Expired - Lifetime US3817657A (en) 1971-11-08 1972-11-08 Integral turbine wheel with axial through-openings at the outer rim and with controlled rim cracks

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US (1) US3817657A (it)
JP (1) JPS4857003A (it)
DE (1) DE2155344A1 (it)
FR (1) FR2160107A5 (it)
GB (1) GB1417132A (it)
IT (1) IT970290B (it)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3897171A (en) * 1974-06-25 1975-07-29 Westinghouse Electric Corp Ceramic turbine rotor disc and blade configuration
US4047837A (en) * 1973-11-16 1977-09-13 Motoren- Und Turbinen-Union Munchen Gmbh Turbine wheel having internally cooled rim and rated breaking points
US4477222A (en) * 1982-09-30 1984-10-16 The United States Of America As Represented By The Secretary Of The Air Force Mounting construction for turbine vane assembly
US20050191181A1 (en) * 2004-02-06 2005-09-01 Snecma Moteurs Rotor disk balancing device, disk fitted with such a device and rotor with such a disk
US20100239422A1 (en) * 2009-03-19 2010-09-23 Honeywell International Inc. Components for gas turbine engines
US20130309097A1 (en) * 2009-03-13 2013-11-21 Rolls-Royce Plc Vibration damper
US20190226342A1 (en) * 2018-01-19 2019-07-25 MTU Aero Engines AG Rotor, in particular blisk of a gas turbine, having a broken-up rim and method for producing the same
US11939877B1 (en) 2022-10-21 2024-03-26 Pratt & Whitney Canada Corp. Method and integrally bladed rotor for blade off testing
US12173614B1 (en) * 2023-08-25 2024-12-24 Pratt & Whitney Canada Corp. Test rotor blade for an aircraft engine blade-off test

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5593274A (en) * 1995-03-31 1997-01-14 General Electric Co. Closed or open circuit cooling of turbine rotor components
AT2429U3 (de) * 1998-07-10 1999-01-25 Jakadofsky Peter Turbinenrad
DE102010042707A1 (de) * 2010-10-20 2012-04-26 Siemens Aktiengesellschaft Bauteil einer Turbine
DE102015111746A1 (de) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Gekühltes Turbinenlaufrad, insbesondere für ein Flugtriebwerk
FR3070965B1 (fr) * 2017-09-13 2019-08-23 Safran Aircraft Engines Moyeu d'helice de soufflante non carenee a zone d'amorce de rupture pour la detection et la prevention des avaries

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2965355A (en) * 1956-01-17 1960-12-20 United Aircraft Corp Turbine disc burst inhibitor
US3255994A (en) * 1963-09-03 1966-06-14 Chrysler Corp Turbine wheel
US3262676A (en) * 1964-05-27 1966-07-26 Chrysler Corp Turbine wheel
US3291446A (en) * 1965-04-13 1966-12-13 Chrysler Corp Turbine wheel
US3395891A (en) * 1967-09-21 1968-08-06 Gen Electric Lock for turbomachinery blades

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2965355A (en) * 1956-01-17 1960-12-20 United Aircraft Corp Turbine disc burst inhibitor
US3255994A (en) * 1963-09-03 1966-06-14 Chrysler Corp Turbine wheel
US3262676A (en) * 1964-05-27 1966-07-26 Chrysler Corp Turbine wheel
US3291446A (en) * 1965-04-13 1966-12-13 Chrysler Corp Turbine wheel
US3395891A (en) * 1967-09-21 1968-08-06 Gen Electric Lock for turbomachinery blades

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4047837A (en) * 1973-11-16 1977-09-13 Motoren- Und Turbinen-Union Munchen Gmbh Turbine wheel having internally cooled rim and rated breaking points
US3897171A (en) * 1974-06-25 1975-07-29 Westinghouse Electric Corp Ceramic turbine rotor disc and blade configuration
US4477222A (en) * 1982-09-30 1984-10-16 The United States Of America As Represented By The Secretary Of The Air Force Mounting construction for turbine vane assembly
US20050191181A1 (en) * 2004-02-06 2005-09-01 Snecma Moteurs Rotor disk balancing device, disk fitted with such a device and rotor with such a disk
US7347672B2 (en) * 2004-02-06 2008-03-25 Snecma Moteurs Rotor disk balancing device, disk fitted with such a device and rotor with such a disk
US20130309097A1 (en) * 2009-03-13 2013-11-21 Rolls-Royce Plc Vibration damper
US8926282B2 (en) * 2009-03-13 2015-01-06 Rolls-Royce Plc Vibration damper
US8157514B2 (en) * 2009-03-19 2012-04-17 Honeywell International Inc. Components for gas turbine engines
US20100239422A1 (en) * 2009-03-19 2010-09-23 Honeywell International Inc. Components for gas turbine engines
US20190226342A1 (en) * 2018-01-19 2019-07-25 MTU Aero Engines AG Rotor, in particular blisk of a gas turbine, having a broken-up rim and method for producing the same
US11939877B1 (en) 2022-10-21 2024-03-26 Pratt & Whitney Canada Corp. Method and integrally bladed rotor for blade off testing
EP4357590A1 (en) * 2022-10-21 2024-04-24 Pratt & Whitney Canada Corp. Method and integrally bladed rotor for blade off testing
US12173614B1 (en) * 2023-08-25 2024-12-24 Pratt & Whitney Canada Corp. Test rotor blade for an aircraft engine blade-off test
EP4513008A1 (en) * 2023-08-25 2025-02-26 Pratt & Whitney Canada Corp. Test rotor blade for an aircraft engine blade-off test

Also Published As

Publication number Publication date
GB1417132A (en) 1975-12-10
IT970290B (it) 1974-04-10
JPS4857003A (it) 1973-08-10
FR2160107A5 (it) 1973-06-22
DE2155344A1 (de) 1973-05-17

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