[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

EP0194957B1 - Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs - Google Patents

Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs Download PDF

Info

Publication number
EP0194957B1
EP0194957B1 EP86630032A EP86630032A EP0194957B1 EP 0194957 B1 EP0194957 B1 EP 0194957B1 EP 86630032 A EP86630032 A EP 86630032A EP 86630032 A EP86630032 A EP 86630032A EP 0194957 B1 EP0194957 B1 EP 0194957B1
Authority
EP
European Patent Office
Prior art keywords
trench
facing surface
stator
fan
wall
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
EP86630032A
Other languages
German (de)
English (en)
Other versions
EP0194957A2 (fr
EP0194957A3 (en
Inventor
Franz Harter
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.)
RTX Corp
Original Assignee
United Technologies 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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP0194957A2 publication Critical patent/EP0194957A2/fr
Publication of EP0194957A3 publication Critical patent/EP0194957A3/en
Application granted granted Critical
Publication of EP0194957B1 publication Critical patent/EP0194957B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel

Definitions

  • This invention relates to axial flow fans/com- pressors of gas turbine engines and particularly to the relationship of the tips of the blades to the adjacent shroud or rub strip.
  • a fan or compressor according to the precharacterizing portion of claim 1 is disclosed in US-A 4 239 452 and in US-A 4 238 170.
  • the tips of the compressor blades extend adjacent the surrounding shroud or rub strip that is trenched or recessed to the dimension complementary to the outer station and tip of the blade.
  • the blades which move radially outward during engine acceleration, machine the groove. Obviously, this technique assures a close fit of the mating parts and helps in avoiding leakage around the tips of the blade.
  • FIG. 1 discloses in Fig. 1 an ambodiment similar to the US patents referred to.
  • Fig. 2 of CH-A 414 681 the trench receiving the blade tips is angularly disposed with respect to the outer flow path surface but the blade tip is parallel with respect thereto.
  • a stator vane is also shown having a tip extending into a trench at the inner flow path wall. The tip of the stator vane and the outwardly oriented surface of the trench are angularly disposed with respect to the inner flow path wall. The vane is adapted to extend deeper into the trench at its leading edge. There is no leakage opposing pumping action against a downstream vertical side wall of the trench.
  • a ducted propeller is disclosed wherein the inwardly facing surface of the trench converges or diverges with respect to the outer flow path surface, but the blade is parallel with respect thereto, thus providing the disadvantage referred to above.
  • GB-A 882 015 the blade tip and the inwardly oriented surface of the trench are angularly disposed with respect to the outer flow path surface.
  • the maximum penetration is at the blade leading edge.
  • GB-A 2 034 435, Fig. 4 wherein a turbine blade tip is shown received in an annular trench in the outer flow path wall. Cooling fluid under pressure is discharged into a cavity formed between the turbine blade tip and the trench to oppose blade tip leakage. The inwardly oriented surface of the trench and a portion of the turbine blade tip are angularly disposed with respect to the outer flow path wall.
  • the object of the invention is to provide a fan or compressor of the type disclosed avoiding or reducing leakage around the blade tip without adversely affecting performance.
  • the blade tip does not penetrate along its full width into the trench when the operating speed causing penetration is obtained.
  • the tip aft portion first penetrates into the trench. This allows deeper penetration without causing too substantial turbulence and accordingly penetration is acceptable at low operation speeds to reduce or avoid leakage in the low speed operating range.
  • the angular contour is designed to effectuate a closure in the gap between the inner wall of the trench and the tip of the blad upon displacement of the compressor and/or fan blade arising out of the growth of the materials resulting from stable hand temperature operating conditions.
  • the invention in its preferred embodiment is illustrated for use in the lower temperature stations of a gas turbine engine and particularly in the compressor section where a soft material circumscribes the engine's inner diameter of the engine case and is abradable so as to be susceptible of being machined by the operation of the rotating blades.
  • a soft material circumscribes the engine's inner diameter of the engine case and is abradable so as to be susceptible of being machined by the operation of the rotating blades.
  • the blades at zero rotational speeds are spaced from the inner diameter of the rub strip and when accelerated to its highest operating speed, cut into the rub strip to define the trench.
  • the trench shape can be machined out prior to engine operation. What is considered the improvement by the teachings of this invention is the particular contour of the tips of the blades and its cooperating trench.
  • FIG. 1 A portion of a compression section 10 of an axial flow compressor of a gas turbine engine is illustrated in Fig. 1.
  • a flow path 16 for working medium gases extends axially through the compression section.
  • An outer wall 18 having an inwardly facing surface to 20 and an inner wall 22 having an outwardly facing surface 24 form the flow path.
  • a plurality of axially spaced rows of rotor blades as represented by the single blades 26 extend outwardly from the rotor 12 across the flow path into proximity with the outer wall.
  • Each blade has an unshrouded tip 28 and is contoured to an airfoil cross section. Accordingly, each blade has a pressure side and a suction side and, as illustrated, has an upstream edge 30 and a downstream edge 32.
  • Extending over the tips of each row of rotor blades is a stator seal land 34.
  • Each land has a circumferentially extending groove or trench 36 formed therein to a depth D at an inwardly facing surface 37 thereof paralleling the
  • a plurality of rows of stator vanes represented by the single vanes 38 are cantilevered inwardly from the stator 14 across the flow path 16 into proximity with the inner wall 22.
  • Each vane which in this illustration has an unshrouded tip 40, is contoured to an airfoil section. Accordingly, each vane has a pressure side and a suction side and, as illustrated, has an upstream edge 42 and a downstream edge 44.
  • Extending over the tips of each row of stator vanes is a rotor seal land 46. Each land has a circumferentially extending groove 48 formed therein.
  • the blade tips 28 are spaced from the inwardly facing surface 37.
  • the gap between tips and surface enables assembly of the components.
  • the rotor tips grow radially outward machining the groove 36 in the abradable material of the stator seal land 34.
  • the point of closes proximity of the blades to the bottom of the groove is referred to as the «pinch point» and normally occurs during a transient engine operating to a maximum speed or power condition.
  • the outer wall including the land moves both axially and radially relative to the blade tips to a position at which the blade tips 28 and inner surface 37 define a gap D.
  • Fig. 2 which is a prior art design is that the blade 50 penetration along its full width into the trench 54 toward the inwardly facing surface 52 as operating speed/increases causes a substantial pumping of air against the trench vertical wall 53 adjacent the blade trailing edge which creates turbulence.
  • the turbulence as shown by arrow A essentially becomes a blockage in the flow path of the gas engine's working medium and adversely affects performance.
  • the maximum depth of blade tip penetration must be controlled to avoid unreasonable turbulence losses at the maximum operating speed. At low speed operating the blade 50 will not penetrate into the trench 54 and leakage can readily occur between the flow path outer wall and the blade tip.
  • the full width of the blade works on the air and has the tendency of over pressurizing this air and hence, creates the undesirable turbulence.
  • the tip of the blade and the inwardly facing surface 37 of the trench 36 are contoured to be angularly disposed relative to the outer gas path wall 18. This is best seen in Fig. 3.
  • the trench 36 is formed to define the contour of the inwardly facing surface 37.
  • the depth of the trench 36 as measured from the inwardly facing surface 20 of the outer wall 18 increases toward the vertical side wall 39 of the tench 36 adjacent the blade trailing edge 32.
  • the axial extension of surface 37 relative to the flow path defined by surface 20 forms angle alpha a.
  • the tip 28 of the blade 26 slants from a given diameter at the leading edge 30 to a higher diameter at the trailing edge 32.
  • Fig. 4 exemplifies another configuration on how the tip can be contoured to combat the leakage problem alluded to in the above.
  • the tip of blade 70 is contoured in a sawtooth fashion providing a plurality of parallel channels 72.
  • the inner surface 74 is angularly disposed to the gas path wall providing similar benefits as was described above.

Landscapes

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

Claims (4)

1. Soufflante/compresseur à flux axial pour turbomoteur possédant des conditions de fonctionnement à haute et basse vitesses, et possédant un stator 14 et un rotor (12) monté à rotation dans le stator (14), un canal de gaz de travail (16) défini entre une surface interne (20) d'une paroi externe (18) dudit stator (14) et une surface externe (24) du rotor (12), le rotor (12) supportant une pluralité d'ailettes (26) s'étendant radialement, comportant chacune une extrémité (28), un bord d'attaque (30) et un bord de fuite (32), une saignée (36) s'étendant circonférentiellement formée dans la face interne (20) de la paroi (18) externe du stator, les extrémités (28) des ailettes étant conçues pour pénétrer dans la saignée (36), ladite saignée (36) possédant une surface interne orientée et une paroi (39) verticale adjacente au bord de fuite (32) des ailettes (26), la face interne de la saignée (36) étant parallèle au contour des extrémités (28) des ailettes, caractérisé en ce que lex extrémités (28) des ailettes et la face interne (37) de la saignée (36) sont disposées angulairement par rapport à la face interne de la paroi externe (18) du stator et sont en biais par rapport à l'axe central de la soufflante/compresseur, la profondeur de la saignée (36), comme mesuré à la face interne (20) de la paroi externe du stator (20) augmentant vers la paroi verticale (39) de la saignée (36), ainsi une partie de bord de fuite de chaque extrémité des ailettes (28) est adaptée pour s'étendre à l'inté-, rieur de la saignée (36) lorsque ladite soufflante/ compresseur (10) est dans un mode de fonctionnement à basse vitesse.
2. Soufflante/compresseur suivant la revendication 1, caractérisé en ce que l'extrémité (28) de chaque ailette (26) est en biais à partir d'un diamètre donné, au bord de fuite (30), vers un diamètre plus important, au bord d'attaque (32).
3. Soufflante/compresseur suivant la revendication 2, caractérisé en ce que le stator (14) possède une direction particulière d'augmentation de dimension, et la direction dudit biais est réalisé dans la direction de l'augmentation de dimension axiale de façon à minimiser l'espace existant entre les extrémités (28) des ailettes (26) et la face interne (37) de la saignée (36) sur l'axe d'augmentation de dimension du stator (14).
4. Soufflante/compresseur suivant la revendication 1, caractérisé en ce que le matériau érodable (34) déposé sur la paroi externe (18) adjacente aux extrémités (28) des ailettes (26) et ladite saignée (36), usiunée dans le matériau érodable (34) par l'accélération de la soufflante/compresseur en condition de fonctionnement à haute vitesse, ou lesdites ailettes (26), s'étendent radialement.
EP86630032A 1985-03-11 1986-03-06 Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs Expired - Lifetime EP0194957B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US71027085A 1985-03-11 1985-03-11
US710270 1985-03-11

Publications (3)

Publication Number Publication Date
EP0194957A2 EP0194957A2 (fr) 1986-09-17
EP0194957A3 EP0194957A3 (en) 1987-06-03
EP0194957B1 true EP0194957B1 (fr) 1990-01-31

Family

ID=24853314

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86630032A Expired - Lifetime EP0194957B1 (fr) 1985-03-11 1986-03-06 Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs

Country Status (3)

Country Link
EP (1) EP0194957B1 (fr)
JP (1) JPS61207802A (fr)
DE (2) DE194957T1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6363726A (ja) * 1986-09-05 1988-03-22 Nippon Shokubai Kagaku Kogyo Co Ltd 表面処理用組成物
EP0528138B1 (fr) * 1991-08-08 1995-05-17 Asea Brown Boveri Ag Anneau d'aube de turbine axiale
DE59201833D1 (de) * 1991-10-08 1995-05-11 Asea Brown Boveri Deckband für axialdurchströmte Turbine.
DE19738671B4 (de) * 1997-09-04 2007-03-01 Alstom Dichtungsanordnung
EP1840332A1 (fr) * 2006-03-27 2007-10-03 Siemens Aktiengesellschaft Aube de turbomachine et turbomachine
WO2014189564A2 (fr) * 2013-03-06 2014-11-27 United Technologies Corporation Rotor comportant une prétranchée pour turbine à gaz
CN112360816A (zh) * 2020-12-08 2021-02-12 成都成发科能动力工程有限公司 一种轴流压缩机承缸和应用其的轴流压缩机

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH221391A (de) * 1939-04-06 1942-05-31 Maschf Augsburg Nuernberg Ag Spaltabdichtungseinrichtung an den Köpfen der Beschaufelung von Strömungsmaschinen, insbesondere Dampfturbinen.
GB882015A (en) * 1957-04-18 1961-11-08 English Electric Co Ltd Improvements in and relating to high speed axial flow compressors
DE1057137B (de) * 1958-03-07 1959-05-14 Maschf Augsburg Nuernberg Ag Schaufelspaltdichtung bei Kreiselradmaschinen mit deckband- oder deckenscheibenlosenLaufraedern
FR1348186A (fr) * 1963-02-19 1964-01-04 Hélice carénée
CH414681A (de) * 1964-11-24 1966-06-15 Bbc Brown Boveri & Cie Strömungsmaschine
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
GB2034435A (en) * 1978-10-24 1980-06-04 Gerry U Fluid rotary power conversion means
US4645417A (en) * 1984-02-06 1987-02-24 General Electric Company Compressor casing recess

Also Published As

Publication number Publication date
EP0194957A2 (fr) 1986-09-17
DE3668661D1 (de) 1990-03-08
EP0194957A3 (en) 1987-06-03
JPS61207802A (ja) 1986-09-16
DE194957T1 (de) 1987-03-19

Similar Documents

Publication Publication Date Title
US4738586A (en) Compressor blade tip seal
EP0781371B1 (fr) Procede de commande dynamique du jeu d'extremites
US5261789A (en) Tip cooled blade
US4239452A (en) Blade tip shroud for a compression stage of a gas turbine engine
EP0792410B1 (fr) Aileron de rotor destine a maitriser les courants de fuite d'extremite
US5476364A (en) Tip seal and anti-contamination for turbine blades
US4238170A (en) Blade tip seal for an axial flow rotary machine
US4645417A (en) Compressor casing recess
EP1895108A2 (fr) Joint abradable d'aile d'ange et procédé de scellage
EP0801209B1 (fr) Dispositif d'étanchéité pour les extrémités des aubes mobiles de turbine
EP3361053B1 (fr) Traitement de tubage de carénage rainuré pour compresseur haute pression dans un moteur à turbine
EP3183428B1 (fr) Aube de compresseur
EP0774050B1 (fr) Structure de stator a rainures circonferentielles interrompues
US20070098545A1 (en) Integrated bladed fluid seal
US4606699A (en) Compressor casing recess
GB1560974A (en) Sealing system for rotors
EP3064709B1 (fr) Plate-forme d'aube de turbine pour influencer les pertes d'incursion de gaz chaude
EP3026215A1 (fr) Rangée d'éléments de surface portante d'un compresseur axial
US20180298912A1 (en) Compressor blades and/or vanes
EP0194957B1 (fr) Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs
US6129513A (en) Fluid seal
US4460309A (en) Compression section for an axial flow rotary machine
GB2324835A (en) Method of manufacturing a turbine blade having discharge holes
GB2161220A (en) Gas turbine stator vane assembly
US12071959B1 (en) Compressor casing with slots and grooves

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE FR GB SE

EL Fr: translation of claims filed
DET De: translation of patent claims
PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): DE FR GB SE

17P Request for examination filed

Effective date: 19870625

17Q First examination report despatched

Effective date: 19880321

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB SE

ET Fr: translation filed
REF Corresponds to:

Ref document number: 3668661

Country of ref document: DE

Date of ref document: 19900308

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19910211

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19910218

Year of fee payment: 6

Ref country code: GB

Payment date: 19910218

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19910228

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19920306

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19920307

GBPC Gb: european patent ceased through non-payment of renewal fee
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19921130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19921201

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

EUG Se: european patent has lapsed

Ref document number: 86630032.0

Effective date: 19921005