8-风险评议相关专利全文us5232339a

1、United States Patent19JPlemmons et al.I 111111111111111111111111111111111111 IIIII IIIII IIIHlllll111111111111111111US005232339A11Patent Number:5,232,33945Date of Patent:Aug. 3, 199354 FINNED STRUCTURAL DISK SPACER ARM75 Inventors: Larry W. Plemmons, Fairfield;Richard A. Wesling, Cincinnati, both of

2、 Ohio73 Assignee:General Electric Company,Cincinnati, Ohio 21 Appl. No.: 826,73222 Filed:Jan. 28, 199251 Int. as. . . FOlD 5/0852 U.S. Cl. . 415/ 178; 415/177;415/199.5; 416/198 A58 Field of Search415/115, 116, 177, 178,415/199.5; 416/95, 198 A, 201 R; 301/6 CS56 References CitedU.S. PATENT DOCUMENT

3、S2,298,333 10/1942 Ash et al. 301/6 cs2,868,439 1/1959 Hampshire et al. .令415/199.52,875,948 3/1959 Stalker415/199.52,889,173 6/1959 Miller 301/6cs3,056,579 10/1962 Bobo.3,074,688 1/1963 De Muth et al415/1773,647,313 3/1972 Koff.3,742,706 7/1973 Klompas415/1153,800,864 4/1974 Hauser et al.4,127,357

4、11/1978 Patterson . 415/1774,213,738 7/1980 Williams. 4,231,704 11/1980 Ayache et al.4,320,903 3/1982 Ayache et al415/178OTHER PUBLICATIONSIntroduction to Stress Analysis, by Charles 0. Harris, 1959, pp. 250-260, The MacMillan Co.Formulas for Stress and Strain, by Roark and Young, Fifth Edition, McG

5、raw-Hill Book Co., pp. 564-572. Theory of Elasticity, by S. Timoshenko, and J. N. Goodier, Engineering Societies Monographs, second edition, pp. 69-73, 1951.Primary Examiner-Edward K. Look Assistant Examine 一r James A. L 还 onAttorney, Agent, or 厅 m- Jerome C. Squillaro; John R.Rafter57 ABSTRACTA rot

6、or disk assembly includes rotor disks and struc tural spacer arms adapted to transmit axial loads and bending moments between adjacent disks. The spacer arms include cooling fms for convective cooling of the spacer arms. The spacer arm is preferably a self support ing wheel structure. The cooling fm

7、s are preferably circumferentially continuous and extend radially into a relatively cooler rotor bore cavity in which the disk hubs are supported. The cooling fms can be positioned on the spacer arms to reduce thermal distortion of the spacer arms, and thereby reduce bending stresses trans mitted to

8、 the disks. The spacer arm includes a body section adjacent a relatively higher temperature seal cavity, which can be purged by cooling air from the relatively lower temperature rotor bore cavity. The temperature differential between the body section and the cooler fm tips results in transfer of cen

9、trifugal hoop loads to the cooling fins, thereby reducing the loads in the spacer arm body section and the amount of cooling air required to purge the higher temperature seal cavity.4,541,775 9/1985 Hovan 416/95 5,157,914 10/1992 Schwarz et al. . 415/11518 Claims, S Dra 血 g Sheets120心/ -心起4242.U S.

10、Patent -二三勹 ,-10Au , 3 193 中 Shet1of5 1 三 、- 30-一二二 _J - - -FIG.,5 232 , 39 1 。PRIOR ART/30埜豆埜立义66起5 vJlIIIIIIIIll II lI IIIIIIIlllI U.S. PatentAug. 3, 1993Sheet 2 of 55,232,339FIG.2PRIOR ARTA ug. 80乙6飞66j.U .S Paten t ,3 1 9 9 3 S he e t 3 0 f S 40砬6V,5 2 3,2 3 3 9 42飞了FIG.3PRIOR ART,3 1 9 9 3 1201

11、2040,.,.4 旷一405 2 3 2 S he e t 4 o f 5 即.U .S Paten t A ug. ,4 FIG.3 3 9 4242Patent ： 尸 / L lLl l80.U.S 12120R6 R15 FIG.-、1、20、A. Aug ,3 1993 飞一 Sheet5 0f S 、B： L.-E232 3, 39 92 1 5,232,339Another advantage of the present invention includes FINNED STRUCTURAL DISK SPACER ARMreduction of thermally ind

12、uced distortions in structuraldisk spacer arms.TECHNICAL FIELDAnother advantage of the present invention is a re- The present invention is related to structural rotor 5 duction in bending stresses in the spacer arms and adja-disk spacer arms in gas turbine engines, and more partic- cent disk rims.ul

13、arly, to a finned structural disk spacer arm arrange-Additionally, a fmned structural disk spacer arm can ment, wherein the finned disk spacer arm is preferably a be provided having fms extending into a lower tempera-ture cooling air cavity in which the rotor hubs are sup-self-supporting wheel struc

14、ture.10 ported.BACKGROUND OF THE INVENTIONStill another advantage of the present invention is a.disk spacer arm cooled without centrifugally loadingRotor constructions in gas turbine engines can in-the disk rim to which the spacer arm is attached.elude a plurality of blade carrying rotordisks separa

15、ted 15Further, spacer arm cooling fms can be provided toby annular disk spacer arms. U.S. Pat. No. 3,647,313, 1:i run cooler than the rest of a self-supporting disk spacerassigned to the General Electric Company, discloses aarm, the fms thereby carrying a portion of the centrifu- com ressor rotor st

16、ruc ure with _disks par ted by gal hoop load that would othe ise be carried by the annular space &?JlS, 9:Ild systen_i for cooling the rotoouter body section of the spacer arm, thereby rlrising construction. It is desirable to minimize the amount ofthe temperature capability of the outer body sectio

17、n of cooling air used to cool rotors and spacer arms in order 20 the spacer arm and reducing the amount of cooling a 江to increase engine cycle efficiency. .required in a cavity outboard of the spacer arm.U.S. Pat. No. 3,056,579, assigned to the General Electric Company, discloses a composite disk st

18、ructure hav-SUMMARY OF THE INVENTIONing a first catenary-shaped portion performing a heat rA structural disk spacer arm for a gas turbine engine shield function, and a second axially aligned stiffening.2,.5, is provided with one or more cooling fms on a radially member, which can have a cylindrical

19、spacer form. inboard surface of the spacer arm. The structural diskCooling fins are shown positioned on the catenary heat spacer can transmit axial loads and bending momentsshield. However, the fmned heat shield of U.S. Pat. No.between adjacent rotor disks. The spacer arm is prefera- 3,056,579 can i

20、ntroduce performance penalties in prac- 30 bly a selfsupporting wheel structure such that wheel tice. Centrifugal loads as well as heat and pressure in- - loads centrifugally generated in the spacer arm during duced loads generated in the catenary shield are trans-maximum engine operating speeds are

21、carried locally by ferred to the disk rims (as discussed in Col. 3, linethe spacer arm, and are not reacted at the adjacent rotor 63-66). This load transfer to the disk rim is due to thedisk rims. The cooling fins are preferably circumferen- fact that the catenary shield is, by design, not a self 35

22、 tially continuous to provide a load pathfor tensile hoop supporting wheel structure capable of carrying its own-loads. The fms can extend into a relatively cool rotor centrifugally induced loads. Therefore, the added cen-bore cavity to run cooler than the rest of the spacer arm trifugal loads due t

23、o the added weight of the finson thestruct?re. The cooler fms tend to shrin relative to t e catenary shield increase the disk rim stress by increasingrest of the spacer arm,_and are preferably_space onthe the centrifugal load transmitted to the disk-rims. Thu 40 isk spa_ce:.to reduce spacin _arm t e

24、rmal distor-the added fi;s on a structure which is not a self-support t!?n d d ks!res es. ca ed _by su:h sp : r arm ing wheel structure can require extra cooling air or disk distortion. Further, by designing circumferentially con- rim material to maintain disk rim stresses at an allowable tinuous fi

25、ns to run cooler than the rest of the spacer level for a given operating temperature. The added arm, the fms are placed in hoop tension and carry a weight of the fins will also increase the hoop stress i;n 45 larger portion of the tensile centrifugal hoop loads thatthe catenary shield.wseocutilodn o

26、tfhtehrewsipseacbere acramrr.ieTdhubsy, btyherehdoutcteinr gotuhteer lbooaddys effFeuctritvheelry, friendsucpeosthiteiormneadl doinsttohretiohnesatinshthieeldstrduoctunroatl and stress in the outer body section of the spacer arm,of the spacer arm is increased, and for a given turbinedisk spacer arm,

27、 and the resultant stresses in the s;pya:c.:e-r: so the temperature capability of of the outer body section arm and adjacent disks. Temperatur gradients in the.)J :o:p_e:r-a:t.i:ng temperature, less cooling air for cooling the disk spacer arms distort disk spacer arms and can resspacer arm is requir

28、ed in a cavity outboard of the spacerin detrimental bending stresses in the spacer arms andarm.adjacent disk rims where the spacer arms transmit bend-ing loads between adjacent disks, especially during 55 BRIEF DESCRIPTION OF THE DRAWINGS transie t operating conditi?ns where the s a r 8?11s - FIG. 1

29、 is a longitudinal cross-sectional schematir.r pond_temperature _ch ges more qui 心 Y thenillustration of a known high bypass gas turbine engine. adjacent disks or connecting flanges._FIG. 2 is an illustration of an enlarged view -of a Additionally, gas turbine en即 eers_ seek to incr eportion of the

30、schematic illustration of FIG. 1, showing turbine operating temperatures for improved engine 60 portions of the high and low pressure turbine sections. efficiency, while maintaining turbine component tem-FIG. 3 is an illustration of an enlarged view of a peratures within allowable I 血 its with a min

31、imalportion of the schematic illustration of FIG. 2, showingamount of cooling air.adjacent rotor disks separated by disk spacer arms.ADVANTAGES OF THE INVENTIONFIG. 4 is a cross-sectional schematic illustration of65 finned disk spacer arms in accordance with thepresent Accordingly, one advantage of

32、the present inventioninvention.is a reduction in the amount of cooling air required toFIG. 5 is an illustration of an enlarged view of the cool a rotor disk assembly.finned disk spacer arm shown in FIG. 4.3 5,232,3394DESCRIPTION OF A PREFERRED69 supported by HPT 29, and enters bore cooling cavity EM

33、BODIMENT60.Referring to FIG. 3, cooling air 66 in cavity 60 bathesFIG. 1 illustrates a known high bypass gas turbine the disk hubs 42 and also cools the disk rims 46 andengine 10. Although shown in cross section, those 5 spacer arm radially inboard surface 83. Annular seal skilled in the art will ap

34、preciate the disclosed axial flow cavities 63 extend circumferentially intermediate flow machine extends circumferentially about engine axis 14. 25 and spacer arms 80. A portion of cooling air 66 can The engine 10 includes a fan 12 for receiving an airflow also be directed as by dovetail slots 47 to

35、 flow beneath18. Disposed downstream of fan 12 are a low pressure blade roots 49, thereby cooling _the_ disk rims 4! andcompressor(LPC) 20, a high pressure compressor 10 purgin_ to_ some extent seal c!viti 63 to !ed ce in es- (HPC) 22, a combustor24, a high pressure turbine tionofhightemperaturegasf

36、low2Sintothecircumfer- (HPT)28andalowpressureturbine(LPT)30. Shaft32 entia1ly extending seal cavities63. Cavities63 ca be connectshighpressureturbine28tohighpressurecom-boundedradiallyoutwardlybyaxiallyandcircumferen- pressor22, whiieshaft34connectslowpressureturbine tiallyextending blade platforms

37、45 and vane plat 缅 30 to low.pressure compressor 20 and ran 12. The fan 15 fo s S ,and bo de! radially inwardl -b r iallrand through LPT 30. The expansion of gas flow 25 in12,compressors 20 and 22, and turbines 28 and 30 are outboard outersurface85 onspacerarms80. Seal cavi- mounted for rotation abo

38、ut a common engine axis 14 inties 63 are in fluid communication with gas flow 25 a manner well known in the art. A portion of airflow 18through the gap between adjacent rotating blade and exiting fan 12 forms fan bypass flow 19 for providingstationary vane platforms 45 and 55, respectively. Seal the

39、 major propulsive thrust of engine 10. The remainder 20 cavities 63 can act as annular buffer cavities intermedi- of airflow 18 forms a core flow 23 which is compressedate high temperature gas flow 25 and spacer arms 80. in turn by compressors 20 and 22. A portion ofthe coreA circumferentially exten

40、ding seal land 98bolted to flow 23 exiting the HPC 22 is burned with fuelin com-the underside of vane platforms 55 faces rotating seal bustor 24 to form a high temperature gas flow 25. Highteeth 96 on circumferentially extending rotating shield temperature gas flow 25 is expanded through HPT 28 25 9

41、2 to restrict the flow of gases 25 inward of platforms 45and 55. Shield 92 can be bolted intermediate adjacentthurobuingehs sh28aftasn3d2 3an0dd3r4iv, ersespcoecmtipvreelsys.ors .22 and 20dcisaknsipnaccluedr earcmirscuamt afebroelntteidallcyosnpnaeccetdiornad9i0al. pSahssiealgdes9924FIG. 2 is an enl

42、arged schematic illustration of a por-30 armfor8d0i,raencdtiningtcoodoolvinetgaailirsbloettsw4e7e.nshield92andaspacertion of engine 10 shown in FIG. 1, showing a d. own-stream portion of HPT 28 and an upstream portion ofEach spacer arm 80 can include a f江st spacer arm endLPT 30. LPT 30 can include a

43、 plurality of rotor disks 4082 integral with an adjacent disk rim 46, a second spacersupported from shaft 34 through shaft extension 36.Each rotor disk can include a hub 42 extending radiallyarm end 84 which can include a radially inwardly ex 匾 tending connecting flange 88, and a circumferentiallyin

44、wardly into a bore cooling cavity 60, a web 44 extend- 35 continuous spacer arm body section 86 extending inter- ing radially outwardly from the hub 42, and a rim 46 inclmudeediaateratdhiealfliy江i nstbaonadrdseicnonnedr esnudrfsa. cBeo8d3y saencdtioanr8a6dicaallny extending radially outwardly from t

45、he web 44 to form outboard outer surface 85.the perimeter of the rotor disk 40. Adjacent rotor disksInner spacer arm surface 83 faces cavity rotor borer: interconne ed by structll: disk pacer s O: 40 cavity 60; while outer spacer arm surface 85 faces seal hich _supp rt adjac_ent r.oto . isk and t an

46、smit a al cavity 63: The temperatiu-e of the gases in cavity 60 are t rust l_?ads P.arted _to _the_ s .ue to the exfansion lowe relative to the temperatures of the gases iii cavity of gas flo_V 25_ t mgh th PT. Th _structu_ral i:iacer 63. The portion of relati ely cool air 66 that is directed a s ca

47、n e- rigi ly attac e? to:. and integral :,vith, an throughdovetail slots 47 helps to purge cavities 63 and a acent s and transmit bending moments between 45 cool the body section 86 of spacerarnis 80, and particu- ad ce_nt disks. . _ larlytheoutersurface85. Totheextentth tthe.portion:f:ac r to d! k

48、40 sl:1pport a_row of blades 48, eacof cooling air 66 directed into seal cavities 63 does not blade 48 including a dovetail shaped root portion 49completely purge cavities63 and some ofgas flow 25 supported i !1shoul er d slot 7disk rim 46, l in aenters cavity 63 spacer arms 80 can separate relative

49、ly anner ell kn?_Wn in the_art Stationa rows ofv es 50 high temperature gas flow 25 from the radially inward 52 extend r_adially inwardly from case 54 intermediatelower temperaturecavity 60. It isdesirably to reduce therowsofrotatingblades48.the amountofcooling air66used topurgecavities63 LPTrotor d

50、isks 40 can be oled y air_ b_!:?_from anandcooloutersurface:.85,sincesuchcoolingairrepre-upstream compressor. A conduit or pipe 62(FIG. l)cansents a performance penalty.carry a portion_()f core ai flow 23 bled from the HPC 55Applicants have found that under engine operating to an opening 53 in case

51、54 surrounding the low pres-conditions thermal gradients in space-r arm-s 80 can sure turbine 30. The bled air, labeled 64 in FIG. 2, is cause the spacer arms to distort by bowing radially relatively low temperature with respect to higher tem- outwardly, as shown in phantom in FIG. 3. The disk 40 pe

52、rature _g_as flow 25. Cooling air 64 enters internaland flanges 88 act as heat sinks, so that the central por- passages 55 in vanes 52. Air 64 cools vanes 52, a portion 60 tion of the spacer arm body section 86 will be at a of which is discharged through vane holes into flow 25. higher temperature t

53、han the spacer arm first and second A portion of air 64 labeled 66 in FIG. 2 passes through ends 82 and 84. The spacer arm body section tempera-apertures 57 in a stationary vane inner structure 51 to ture will also increase radially outwardly from inner enter a n annular chamber 61, which can be bou

54、nded surface 83 (which faces relatively low temperature air upstream by an HPT rotor disk 29, and downstream by 65 in cavity 60) to outer surface 85 (which faces relatively stationary annular seal 68 extending radially inward higher temperature air in cavity 63). The resulting from structure51. Cool

55、ing air 66 passes through a radial spacer arm distortion is detrimental. The spacer arm is a clearance between stationary seal 68 and rotating seal structural component that can transmit both forces and6 5 5,232,339bending moments between adjacent disks, and thermalThe fins 120 are preferably circumferentially continu- distortion of the spacer arm can result