EP0321825B1 - Rangée d'aubes rotoriques pour traversée axiale pour compresseurs ou turbines - Google Patents

Rangée d'aubes rotoriques pour traversée axiale pour compresseurs ou turbines Download PDF

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Publication number
EP0321825B1
EP0321825B1 EP88120768A EP88120768A EP0321825B1 EP 0321825 B1 EP0321825 B1 EP 0321825B1 EP 88120768 A EP88120768 A EP 88120768A EP 88120768 A EP88120768 A EP 88120768A EP 0321825 B1 EP0321825 B1 EP 0321825B1
Authority
EP
European Patent Office
Prior art keywords
rotor
disc
blade
foot
blades
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
EP88120768A
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German (de)
English (en)
Other versions
EP0321825A2 (fr
EP0321825A3 (en
Inventor
Gerd Luxenburger
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 GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0321825A2 publication Critical patent/EP0321825A2/fr
Publication of EP0321825A3 publication Critical patent/EP0321825A3/de
Application granted granted Critical
Publication of EP0321825B1 publication Critical patent/EP0321825B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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

  • the invention relates to an axially flowed rotor blade grille according to the preamble of patent claim 1.
  • Blade grilles according to the type mentioned have proven themselves in practice, with regard to the control of the peripheral force and tension loads to be expected at relatively high speeds and centrifugal forces on the rotor, and with regard to the achievability of a comparatively low wheel disc weight.
  • a previously discussed blade configuration of axially at a distance above the wheel disc or the wheel rim and in the circumferential direction protruding from the foot contour is known from FR-PS 12 07 772; the should be inserted into the axial grooves Sit the blades by means of a nose protruding radially at the bottom on the wheel rim end faces in question, axially fixed in one direction.
  • sealing plates extending in the circumferential direction should be anchored between grooves running on the inside of the footplate and circumferential grooves machined on the wheel rim side.
  • the known case also provides a cover disk which also rotates with the wheel disk, via which cooling air branched off from the compressor end is to be supplied to the relevant airfoils on the one hand via the blade feet and on the other side on the end face, flowing radially inward along the wheel disk.
  • the noses mentioned had the following disadvantages: additional manufacturing and processing effort for the blades; possible component temperature increase due to air friction; structurally restricted cooling air supply, if in particular the blade cooling air is to be supplied on the base of the groove; About the lugs radially upward relatively far-reaching formation of the cover plate to form a smooth or uninterrupted contact surface on the wheel rim, on the end face, for which the cover plate also forms the blade lock acting in a different axial direction.
  • sealing plates lead to increased manufacturing and assembly costs, especially since - as is often the case - they are additionally to be anchored in the circumferential direction against rotation on the wheel rim, e.g. B. by means of tension wires. Such sealing plates also lead to local disc weight increases and additional loads on the wheel disc and blades.
  • EP-A-068923 or US-A-4,527,952 of the same patent family (each of which forms a generic part for the introductory part of patent claim 1), deals in various embodiments with axial securing on both sides of its lower dovetail-like foot ends (FIGS. 1-5 ) blades to be inserted in adapted axial grooves; these have foot plates (FIG. 4) which extend over the entire axial blade length and in each case on both sides of the blade blade and a so-called "central shaft" above the wheel rim (bump) in mutual support of centrifugal force on.
  • foot plates FIG. 4
  • the blade is secured by means of a locking member which is dimensioned to match the groove geometry or is oversized with respect to the radial installation height compared to the geometry of the blade root end; anchored radially in the center in the groove (FIG. 1) of the blade root, the locking member should be insertable into the axial groove together with the foot end; by raising the blade and the foot by means of a wedge (FIG. 3) from the base of the groove, the link should at the same time be able to be latched into recesses (FIG. 1) of adjacent disc bumps; it can be provided with two end faces of the wheel rim screwed retaining plates (Fig. 4) for axial wedge locking or sealing.
  • a further variant (FIG. 5) of the known case provides holding plates attached to both outer end faces of the foot end; these are dimensioned to be axially retractable into the axial groove and overlap corresponding end faces of the wheel rim (hump) after the raidal has been raised by means of the wedge.
  • a further variant (FIG. 7) of the known case on the blade shaft - between the foot end and the platform - provides laterally projecting lugs on shoulders; In a predetermined position (Fig.
  • the blade can only be axially secured on both sides between two axially successive additional bumps, which are arranged on the disc bumps, after the blade has first been pushed through the adapted axial slots of the additional bumps and then the shovel at the foot end has been raised radially upwards by the wedge.
  • Significant disadvantages of the known case Relatively complicated assembly (wedge); Axial locking required for wedge; local weakening of the foot, in particular with regard to the movable securing element (FIGS. 2 and 3); locally relatively low "material meat incorporation" in the rim; Additional sealing arrangements through special components (sheets - Fig. 4); from the screwing of these sheets and in particular from the variant with so-called haite plates (FIG. 6) there is a risk of locally increased air or Gas friction, and thus component temperature increase; hindrance of a cooling air supply (turbine blades), here in particular in each case by means of a wedge arrangement.
  • US-A-3,378,230 deals with the assembly and fastening of rotor blades equipped with base plates on the wheel rim of a wheel disc; the base plates (FIG. 1) are always arranged with axially open spaces opposite the wheel rim surface; with lower dovetail-like foot ends, the blades can be inserted in the axial direction in appropriately adapted axial grooves which are recessed radially deeper on the base of the groove base; A radial axial attachment and securing of the blade on the foot side is only possible in a radially raised blade position via a locking plate inserted between the bottom of the groove and under the foot end; the locking plate should be anchored by means of tongues bent radially upward against the wheel rim end faces.
  • JP-A-226-202 can be interpreted in accordance with the present abstract in such a way that in the case of a dovetail-shaped foot-groove anchoring of turbine blades, as an axial securing device in one direction, a step which engages step-wise into the wheel disk flesh at the lower end of the foot should be provided.
  • the invention has for its object to provide a blade grille according to the type mentioned, in which the blades on relatively axially secured in one direction on a wheel disc.
  • the relevant length dimension of the respective blade feet can be assigned very precisely to the corresponding length dimension of the axial grooves or recesses in the wheel disk. Furthermore, there are no local component gradations on the wheel disc, between the disc bumps and the blade roots, which would have to be bridged locally by a cover disc provided on the end face of the wheel disc for guiding the cooling air. In connection with the supply of cooling air to the blades, an optimal frontal seal between the cover disk and the respective disk counter surface is achieved.
  • Another important advantage of the invention is that precise machining of the root of the blades or disk in question is not hindered.
  • cooling air supply from below is never hindered by the relevant feet of the rotor blades.
  • the cooling air supply is thus together with one or two cover plates to the turbine blades from below through the foot of one or both sides of the wheel disc unhindered.
  • FIG. 1 to 4 there is an axially flowed rotor blade grille of a turbine, in particular a gas turbine jet engine, in which the rotor blades 1 with their feet 2 on axial grooves 3 of the wheel disk (FIG. 2) which are spaced apart geometrically and are spaced apart from one another (FIG. 2) 3 and 4) are held, wherein component overlaps N (FIGS. 1 and 4) are formed in one direction between the base-side sections of the blades 1 and the wheel disk 4 as axial blade securing means.
  • the disk-anchored rotor blades 1 between the blade root plates 5 and the wheel disk surface include spaces extending in the axial and circumferential directions (FIGS.
  • the present exemplary embodiments provide customary bidentate composite rotor blades without, however, being bound to such a foot geometry.
  • the relevant foot geometry can e.g. hammer head-like or, as shown in Fig. 1,3,5 etc., be designed like a pine cone or a fir tree foot.
  • a part of the disc bumps 8 in question (FIG. 2) in the upper or outer region can be processed accordingly, with the webs 7 being formed.
  • the processing mentioned can be carried out, for example, by turning.
  • the wheel disc 4 (FIG. 2) can also be manufactured beforehand in the sense of the required nominal size.
  • the wheel disk 4 in question can be produced from the outset, for example, electrochemically or as part of a pressure sintering process in the context of the required nominal size or the precautions for the formation of the webs 7, suitable surface finishing to the required nominal size optionally being able to be carried out by machining or grinding finishing .
  • the webs 7 in question are nose-shaped and each extend parallel to the front faces of the nasal bumps 8.
  • the radial wall parts of the moving blades 1 in question that is to say, for example, the radial wall part 6 on the base plate 5, which is at the rear here, can be spatially aligned recesses 9 drawn in on the inside to receive the relevant counter sections of the webs 7 on the wheel disk 4.
  • each turbine blade 1 has at least two axially spaced radial front and rear wall parts 6 ′ and 6, which extend over the entire width of a base plate 5; As can be seen from FIG. 3, the rotor blade 1 thus forms stop surfaces against the relevant webs 7 on the wheel disk 4 via the rear wall part 6 on both sides of the wheel disk surface in the circumferential direction.
  • the associated component overlaps N can be relatively small; they are dependent on the sum of the tolerances at the relevant mutual contact points, the centrifugal force and the thermal expansions of the blade, the deflection of the relevant web 7 on the wheel disk 4 by axial forces and also on the surface pressure between the relevant web 7 and the rotor blade 1.
  • the above-mentioned webs 7 on the wheel disk 4 extend here in the middle circumferential area along the surfaces of the disk bumps 8 in question.
  • a blade design can be represented that has a comparatively large one at the downstream end axially projecting roof-shaped overhang with the base plate 5. Accordingly, there is a comparatively narrow circumferential channel section between the two radial wall parts 6 and 6 ', locally above the wheel disc surface formed by the cusps 8.
  • the wheel disk 4 is assigned a cover disk 10 which also rotates on the end face and which, in the sense of FIGS. 2 to 6, is also intended to fix the rotor blades 1 'to be cooled in the wheel disk 4 on the webs 7 in the axially opposite direction.
  • the cover disk 10 With the outer component section 10 ', the cover disk 10 is seated correctly on the end face on the relevant mating surfaces of the radial wall parts 6', the disk hub core 8 (FIG. 2) and the blade roots 2.
  • the cover disk 10 forms a cooling air chamber 11 along the wheel disk 4, which is connected to the moving blades 1 'of the moving grille from the relevant blade root sides via suitable coolant lines 12, 13 (cooling air flow from F to F').
  • the chamber 11 is thus e.g. Air taken at the high-pressure compressor end, which is supplied via the hollow shaft system of the high-pressure compressor;
  • spaces between the respective base plate 5 and a front and rear wall part 6 ', 6 and the wheel disk surface can be formed for guiding the cooling air into the rotor blades 1' (airfoil blades).
  • FIGS. 11 to 14 differs from that according to FIGS. 2 to 6 in that at the rear end of the turbine blade 1, in the region of the rear wall part 6 and between the local end of the base plate 5 and foot 2, a relatively large-area recess 12 is formed, into which the webs 7 protrude locally (FIG. 13).
  • cover disks shown in FIG. 9 instead of the cover disks shown in FIG. 9, other additional disk-shaped securing elements (co-rotating) can also be provided, which do not have to be related to a coolant guide chosen as an example in accordance with FIG. 9.
  • FIG. 15 and 16 once again illustrate a variant, for example in the form of rearward engagement of the webs 7 in the relevant recesses 9 (see also FIG. 6), the rear radial wall parts 6 in question abutting the webs 7.
  • the blade root grooves 3 are each inclined at the same angles with respect to the disk axis in question.
  • Such inclined or inclined grooves 3 are used as an example in all the previous embodiments.
  • the axial or foot grooves could of course also be arranged axially parallel.
  • cage variants mentioned by way of example can also be designed such that the component overlaps N form a local secondary flow seal with respect to the air flow in the compressor duct (compressor rotor blades) or with respect to the hot gas flow in the turbine duct (turbine rotor blades).
  • the component overlaps N can form a local cooling air shutoff seal with respect to the hot gas flow in the turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sliding-Contact Bearings (AREA)

Claims (9)

  1. Rangée d'aubes rotoriques à traversée axiale pour compresseurs ou turbines, en particulier de réacteurs à turbine à gaz, dans laquelle les aubes rotoriques (1) sont maintenues par leurs pieds (2) au niveau de gorges axiales (3) du disque de roue (4), lesdites gorges axiales (3) possédant une géométrie appropriée et créant des bosses de disque (8) espacées les unes des autres, des chevauchements (N) de composants étant réalisés entre les parties de pied (5) des aubes et la surface supérieure du disque de roue pour immobiliser axialement les aubes, et les aubes rotoriques (1) comprenant, entre des plaques de pied d'aube (5) et la surface supérieure du disque de roue, des interstices qui s'étendent dans les directions axiale et circonférentielle, caractérisée en ce que les plaques de pied (5) comportent des parties radiales (6, 6') de paroi, et en ce que les chevauchements (N) des composants sont formés au niveau des interstices entre une partie radiale (6, 6') de paroi et des nervures (7) situées sur les bosses de disque (8), lesdites nervures étant en forme de talon et pénétrant radialement dans les interstices à partir de la surface supérieure du disque de roue.
  2. Rangée d'aubes rotoriques selon la revendication 1, caractérisée en ce que les contours extérieurs respectifs des nervures (7) et d'une partie de paroi (6) se chevauchent mutuellement dans la position d'immobilisation axiale, dans laquelle le contour des nervures peut être formé par les contours libres (R) de gorges axiales voisines (3), lesdits contours libres (R) étant prolongés géométriquement vers l'extérieur sur le côté disque, et le contour de la partie de paroi (6) peut être formé par les contours de contact (S) du pied d'aube correspondant (2), lesdits contours de contact (S) étant prolongés géométriquement vers l'extérieur sur le côté disque.
  3. Rangée d'aubes rotoriques selon la revendication 1 ou 2, caractérisée en ce que la partie radiale (6) de paroi d'une plaque de pied d'aube (5) comporte des évidements (9) spatialement en retrait vers l'intérieur, pour recevoir les portions correspondantes des nervures (7).
  4. Rangée d'aubes rotoriques selon une ou plusieurs des revendications 1 à 3, caractérisée en ce que chaque aube (1) comporte des parties radiales avant et arrière (6', 6) de paroi qui s'étendent sur la plaque de pied (5) dans la direction circonférentielle et dont la partie avant ou arrière (6', 6) forme, de chaque côté du pied d'aube (2), le recouvrement (N) de composants.
  5. Rangée d'aubes rotoriques selon une ou plusieurs des revendications 1 à 4, caractérisée en ce que les extrémités avant et arrière de la plaque de pied (5) de chaque aube rotorique (1) dépassent des parties radiales (6, 6') de paroi dans la direction axiale à la manière d'un toit.
  6. Rangée d'aubes rotoriques selon une ou plusieurs des revendications 1 à 5, caractérisée en ce que le disque de roue (4) est associé, de manière connue en soi, à un disque de recouvrement (10) qui tourne avec lui en position frontale et qui immobilise, dans le sens opposé axial, les aubes rotoriques (1') qui sont montées dans le disque de roue (4) contre les nervures (7).
  7. Rangée d'aubes rotoriques selon la revendication 6, comprenant des aubes rotoriques refroidies de turbine, caractérisée en ce que le disque de recouvrement (10) forme, de manière connue en soi, le long du disque de roue (4), au moins une chambre d'air de refroidissement (11) qui est reliée aux aubes rotoriques (1') à refroidir, par l'intermédiaire de conduites appropriées (12, 13) d'agent de refroidissement.
  8. Rangée d'aubes rotoriques selon une ou plusieurs des revendications 1 à 7, caractérisée en ce que les chevauchements des composants forment un joint local d'écoulement secondaire par rapport à l'air du compresseur ou au gaz chaud.
  9. Rangée d'aubes rotoriques selon la revendication 7, caractérisée en ce que les chevauchements des composants forment un joint local d'arrêt de l'air de refroidissement par rapport à l'écoulement du gaz chaud dans la turbine, des interstices compris entre la plaque de pied (5) ainsi que les parties radiales avant et arrière (6', 6) de paroi et la surface supérieure du disque de roue pouvant ainsi être prévus pour amener l'air de refroidissement dans les aubes rotoriques (1').
EP88120768A 1987-12-19 1988-12-13 Rangée d'aubes rotoriques pour traversée axiale pour compresseurs ou turbines Expired - Lifetime EP0321825B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19873743253 DE3743253A1 (de) 1987-12-19 1987-12-19 Axial durchstroemtes laufschaufelgitter fuer verdichter oder turbinen
DE3743253 1987-12-19

Publications (3)

Publication Number Publication Date
EP0321825A2 EP0321825A2 (fr) 1989-06-28
EP0321825A3 EP0321825A3 (en) 1989-08-30
EP0321825B1 true EP0321825B1 (fr) 1992-12-16

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Application Number Title Priority Date Filing Date
EP88120768A Expired - Lifetime EP0321825B1 (fr) 1987-12-19 1988-12-13 Rangée d'aubes rotoriques pour traversée axiale pour compresseurs ou turbines

Country Status (5)

Country Link
US (1) US4940389A (fr)
EP (1) EP0321825B1 (fr)
JP (1) JP3120849B2 (fr)
DE (2) DE3743253A1 (fr)
ES (1) ES2036662T3 (fr)

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EP1916389A1 (fr) * 2006-10-26 2008-04-30 Siemens Aktiengesellschaft Assemblage d'aubes de turbine
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US9145772B2 (en) 2012-01-31 2015-09-29 United Technologies Corporation Compressor disk bleed air scallops
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FR3015553B1 (fr) * 2013-12-23 2019-05-31 Safran Aircraft Engines Aube comprenant une echasse, munie d'une seule portion en depression
GB202114772D0 (en) * 2021-10-15 2021-12-01 Rolls Royce Plc Bladed disc
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Also Published As

Publication number Publication date
JP3120849B2 (ja) 2000-12-25
ES2036662T3 (es) 1993-06-01
DE3743253C2 (fr) 1991-04-25
DE3743253A1 (de) 1989-06-29
JPH01193005A (ja) 1989-08-03
DE3876768D1 (de) 1993-01-28
US4940389A (en) 1990-07-10
EP0321825A2 (fr) 1989-06-28
EP0321825A3 (en) 1989-08-30

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