3-筛选及标引后的专利著录项目数据及专利全文us4805398a

1、United States Patent191Jourdain et al.11Patent Number:4,805,39845Date of Patent:Feb. 21, 198954 TURBO-MACHINE WITH DEVICE FOR AUTOMATICALLY CONTROLLING THE RATE OF FLOW OF TURBINE VENTILATION AIR75 Inventors: Gerard E. A. Jourdain, CorbeilEssonnes; Jean M. Payen, Le Mee sur Seine; Georges Mazeaud,Ye

2、rres, all of France73 Assignee:Societe Nationale dEtude et deConstruction de Moteurs dAviation S. N. E. C. M.A., Paris, France21 Appl. No.: 103,41722 Filed:Oct. 1, 198730Foreign Application Priority DataOct. I, 1986 FRFrance86 1367151 Int. Cl.4 .F.0.2.C 3./00; F02C 5/0052 U.S. Cl. . 60/39.75;416/95;

3、415/47; 415/116; 236/93 R 58 Field of Search60/ 39.75, 39.83, 39.32;416/95; 415/116, 47, 175; 236/93 R, 101 R56 References CitedU.S. PATENT DOCUMENTS 1,557,197 10/1925 Dickey.2,811,833 11/1957 Broffitt . 415/1163,029,064 4/1962 Buckingham.3,078,671 2/1963 Senser.3,814,313 6/1974 Beam, Jr. et al 415/

4、 1163,966,354 6/1976 Patterson 415/1163,975,901 8/1976 Hallinger et al.415/1154,109,864 12/1976 Clayton.4,213,738 7/1980 Williams . 416/954,217,755 8/1980 Williams 60/ 39.75FOREIGN PATENT DOCUMENTS 56172762 5/1983 Japan.712346 7/1954 United Kingdom. 923789 4/1963 United Kingdom.Primary Examiner-Dona

5、ld E. Stout Attorney, Agent, or Firm Obion, Fisher, Spivak,McClelland & Maier57 ABSTRACTA device for automatically controlling the rate of flow of turbine ventilation air in a turbo-machine comprises two superimposed ceramic rings which are split and are each fixed at a single point to a metal suppo

6、rt so that differential expansion of the support and the two rings in response to the operating conditions of the turbo machine causes the registry of peripherally disposed slots in the ceramic rings to vary and thereby control the rate of ventilation air flow therethrough in accor dance with the tu

7、rbo-machine operating conditions.10 Claims, 6 Drawing SheetsFIG. 101 U.S. PatentFeb. 21, 1989Sheet 1 of 64,805,398U.S. PatentFeb. 21, 1989Sheet 2 of 64,805,398FIG. ZFIG. 3A k U.S. PatentFeb.21, 1989Sheet 3 of 64,805,3982323b，们户，I I 1 : I，1,1i!。1, II-Il I n1 23 j1 nu ( ( U.S. PatentFeb.21, 1989Sheet

8、4 of 64,805,398 , . 2 a , , u _, -I 6 l - ) J 孙I_I1 ( 23一价，仁们一1_1 1 3 , IC 1, | (111111 , II_l_ ilI ( /111111 I，1, 1 1- )l FIG.Sbii-_ i-卢 g-I1. I一亏了 歹，IS FIG. 6c，li_W I; !i、一二I I I I I, II- S2r H |！，i，1 甘， I,.，I- : 。c b / F/G.6b / / / / - / z FIG. 6aFIG. 7103b、44、! 二.U.S Paten t ,4 8 0 5 3 9 8 S hee

9、 t 5 0 f 6 Fe .b 2,1 1 9 8 9 127 FIG. 8 U.S. PatentFeb. 21, 1989Sheet 6 of 64,805,398257、 FIG. 9FIG. 101 TURBO-MACHINE WITH DEVICE FOR4,805,3982 specific consumption in certain phases of flight, this being an essential parameter for such aircraft. The modAUTOMATICALLY CONTROLLING THE RATE OF FLOW OF

10、 TURBINE VENTILATION AIRulation can thus be applied to the part-load operating stages, which represent an appreciable proportion of5 the operating time, possibly in excess of 80%.BACKGROUND OF THE INVENTIONAccordingtotheinventionaturbo-machine havinga(1) Field of the Inventiontur ine _ventilation ai

11、r_ upply sy _t_em i provide_with Toe invention relates to a turbo-machine device fordevice for automatically controlling the rate of flow of automatically controlling the rate of flow of turbinethe turbine ventilation air comprising two radially su- ventilation air.-10 perimposed rings mounted conce

12、ntrically on a support Research on improved performance in modern turbo- and disposed in the ventilation air supply system, each machines has resulted in an increase in operating tem- ring being open at a transverse slit and being fixed to peratures, in turn requiring new materials satisfyingsaid su

13、pport at a single point diametrically oppositethe these conditions of use. The control of thermal expan-transverse slit, the fixed points of the two rings being sion and the need for improved operational behaviour 15 diametrically opposite one another, each ring having a and increased length of life

14、 of components has also ledplurality of slots which are uniformly distributed to a need for complex cooling systems which, in partic- around its periphery, and the material from which the ular,use air bled from the cold parts of the machine tosuperimposed rings are made having a coefficient of venti

15、late hotter parts, such as the turbine for example.thermal expansion which is distinctly different from Technical development has in fact been accompanied 20 that of the aterial from which the support is made, theby asu_bstantial increase in the temperatures at the tur-arrangement being such that th

16、e slots in the two rings bine inl t._ _ _ _ _either register with each other to provide a maximum O e _fa tor - ich also infl ences _perfo ance, anventilation air flow, are completely offset from onepa!ticu; ly_ effic en y or maxjm m _tl rus: _in aer mauti-., another to shut off the ventilation airf

17、low altogether, or cal applications, is the control of minimal but adequate 25 ;a;r-e;in an intermediate, partly registering, position to clearance between stationary and rotating.parts of th provide a modulated ventilation air flow, depending on turbo-machine. One of the means conventionally used t

18、he thermal expansion of the support caused by theto match the radial expansion or contraction of a stator operating conditions of the turbo-machine.element at a radial end of a rotating part (a rotor bladeor element) to the radial movements of said end is to 30 provide ventilation for the stator ele

19、ment.;:_-:vIt will therefore be apparent that control of the rates of flow of ventilation air is an important factor in con- trolling the operating conditions of a turbo-machine, irrespective of the use of such air, two examples of 35 which are indicated above in connection with the cool- ing of the

20、 turbine elements or adjusting the operational clearances between the rotor and stator.(2) Summary of the Prior ArtThe way in which the passage area defined by the partial registration of the slots, which determines the rate of air flow, varies with temperature can advanta- geously be varied by appr

21、opriate selection of the shape of the slots.Preferably, the support is made from a metallic mate- rial, and the superimposed rings are made of a ceramic material having a coefficient of thermal expansion dis- tinctly less than that of the support material.Advantageously, the superimposed rings of th

22、e con-u.S. Pat. No. 3,975,901, for example, describes a 40trol device can be disposed in the air cooling circuit of device which meters a mixture of two gas flows at a turbine rotor stage or in a stator ring ventilation cir- different temperatures, the mixture being applied to a cuit in order to adj

23、ust the clearances between the rotor turbine stator wall by means of a shutter -wiifch moves an th stator, _or they a be d_ispo_sed the up trea1? radially with respect to two gas passages, the movement e d ?f a_ turbine ventil tion _ circuit, adjacent the airbeing produced-by thermal- expansion. How

24、ever, the 45 bl _? i the c_ompr - s?r housing.use orsuch a devi e is a sensiti e and complex matterThe i_nvention will be_ more readily u_1_1_derstood, and and requires the use of two gas sources at differentother characteristics and advantages_ will be apparent, temperatures.-from the following des

25、cription of various embodiments u.s. Pat. No. 3,029,064 describes means for control-of the invention with reference to the accompanyingling the supply of air to cooling chambers disposed 50 drawings.around a turbine casing comprising butterfly valves, theBRIEF DESCRIPTION OF THE DRAWINGS movement of

26、 which is controlled by the differentialexpansion of a ring divided into cylindrical segments,FIG. 1 is a partial half-view, in _longitudinal section each associated with a valve and having one end se- through the turbo-machine axis, of a turbine provided cured to the casing and the other connected

27、to the 55 with a ventilation airflow control device in accordance valve. This device uses a plurality of valves, the lack of with the invention applied to a cooling air supply circuit reliability of which may jeopardise its efficiency.of a rotor stage;FIG. 2 is a partial perspective view to an enlar

28、gedSUMMARY OF THE INVENTIONscale of tletail II in FIG. 1 showing the mounting of twoThe object of the invention is to provide automatic 60 superimposed rings on a support in the air flow control control of the ventilation air flow rates in a turbine device;without the disadvantages of the known cont

29、rol de-FIG. 3 is a partial transverse view of the support vices. One important advantage of this automatic con- shown in FIG. 2;trol is that it allows the rate of flow of turbine ventila-FIGS. 4a and 4b are diagrammatic cross-sections tion air to be permanently matched, during operation, 65 transver

30、se to the turbine axis showing the mounting of to utilization requirements, for example flight needs in the two superimposed rings on the support, at a cold the case of aeronautical application to a turbo-jet engine temperature and at a hot temperature after thermal of an aircraft. This results in a

31、n appreciable reduction of expansion of the support;4 3 4,805,398FIGS. Sa and Sb are partial developed top plan viewsference of 12 X 10-6 mm per degree C. between the of the superimposed rings used in the device shown incoefficients of thermal expansion. Each ring 22 or 23 is FIG. 1, at cold and hot

32、 temperatures;open and has a transverse slit 22b or 23b, as will be seen FIGS. 6a, 6b and 6c are diagrams illustrating differentin FIGS. 4a, 4b, Sa and Sb, and each ring is connected forms of slots which may be used in the superimposed 5 to the support at just one point which is thus a fixed rings i

33、n the device shown in FIG. 1;point indicated at 22c and 23c in FIGS 知 and 4b, the FIG. 7 illustrates graphically the variation of thecircumferential relative movements between the rings passage section in the slots shown in FIGS. 6a, 6b, 6c as22 and 23, on the one hand, and their supports, on the a

34、function of temperature;other hand,retaining complete freedom outside the FIG. 8 is a partial half-view, in _longitudinal sec_tion 10 respective fixed points. FIG. 知 diagrammatically through the turbo-machine axis, of a turbine providedshows two rings 22 and 23 mounted concentrically and w!th a_ ve

35、tilation airflJ. c?.ntrol d vic_e i acc_ordan ein radial superimposition on a support. The respective with the invention and similar to the device shown infIXed points ofeach ring 22c and 23c are diametrically F:IG._1, a J?lied to co t:ol r:idial mov:ments of_ a stator _ _ opposite one another, a d

36、the slits 22b and 23b are re rin for adjustment of the clearances between the rotor 15 sp ctively diametric lly opposite the fixed points andand stator;also diamet 如 ally opposite one another. The rings are FIG. 9 is a partial half-view in longitudinal section of shown in a cold state in FIG. 知 ， i.

37、e. in the absence of a turbo-machine compressor at the air bleed intended any appreciable thermal expansion, and FIG. 4b illus-for ventilation/cooling of the turbine and comprising a trates the position of the rings when hot, the degree offlow control device in accordance with the invention; 20,.d;i

38、splacement being exaggerated in order to facilitateand,FIG. 10 is a partial view in transverse section of the device shown in FIG. 9.25DESCRIPTION OF THE PREFERRED EMBODIMENTSunderstanding. FIG. 4b shows the position after thermal expansion of the support from a radius R to a radius R. At the slits

39、22b and 23b each ring end has thus moved an amount d=1T(R-R), and a point A on the ring 22 and a point B on the ring 23 situated half-way between theReferring to FIG. 1, a turbine in accordance with thefixed points and the slits in the cold state shown in FIG.invention as partially illustrated compr

40、ises an inlet=知-ha:v;:e: respectively moved as shown in FIG. 4b in guide stator 1 and a rotor stage 2 which are mounted opposite directions to one another to Aand B, each inside an outer turbinecasing 3.30 through a distance d/2=1r/2(R-RR). Thevariations The stator 1 comprises guide vanes 4 mounted

41、be-obtained as a function of the temperature differencestween a radially outer sleeve S and a radially inner AT and the coefficient of thermal expansion Aa are:sleeve 6. The outer sleeve 5 is secured to the casing 3 bymeans of upstream radial flanges 7 and downstream radial flanges 8, and is connect

42、ed by further flanges to 35 the outer jacket 9 of the combustion chamber 10 up- stream thereof, the terms upstream and downstream being used with reference to the normal direction of movement of the main flow of the gases of the turbo- machine. The turbine casing 3 is also connected by 40 upstream f

43、langes to the outer combustion chamber cas- ing 11 On the inside the stator 1 has a peripheral vane root 12 which on the upstream side is fixed on a flange 13 of the inner jacket 14 of the combustion chamber which together with an inner casing 15 of the chamber 45 defines an inner combustion chamber

44、 enclosure 16. On the downstream side, the inlet guide vanes 4 similarlyR-R=RxaaxaTAs will be seen from FIGS. 2 and 3, the flange 13 has cut-outs 24 which are distributed uniformly around the flange, and similarly the radial flange 19 has co-operat- ing cut-outs 2S which are also uniformly distribut

45、ed peripherally.Furthermore, downstream, the rotor stage 2 of the turbine comprises a disc 26 on which the movable blades 27 are mounted in sockets 26a. At the tips of the blades 27 the stator conventionally has a sealing ring 28 secured to the turbine casing 3 by a radial flange 29 and a support ri

46、ng 30. Upstream, a disc 31 is also associated with the rotor disc 26, the disc 31 bearing labyrinth sealshave a peripheral root 17. The in er casing lS continuesa d 33_ an _bein_g orm d with bores 34 which are upstream in the form of an annular collar 18 which isdis_!_r:ibuted uniorm!y i a r:ing.con

47、nected to the downstream edge of the inner stator soThe above-describe_d turbine comprises_ a ventilationsleeve 6 and to the downstream peripheral root 17. A path for air-coolin_g _the roto_r _stage 2 and particular! radial flange 19 is secured to the inner downstreamthe sockets 26a of the disc 26 a

48、nd the blade roots 27 combustion chamber flange 13 and is thus secured to themounted therein. The air flows along this ventilation peripheral root 12.path are controlled by the device in accordance with The downstream surface of flange 19 has a peripheral 55 the invention, which operates as. follows

49、. The cooling groove 20, and the peripheral root 17 also hasa periph-air is bled from the combustion chamber enclosure 16 eral groove 21 on its upstream surface facing the grooveand passes through the cut-outs 24 and 2S in the flanges20. Two radially superimposed and concentric rings 22 13 and 19 to

50、 enter an annular enclosure 3S formed be- and 23 are fitted in the grooves 20 and 21. The rings 22 tween the superimposed rings 22 and 23 and the inner and 23 are formed with slots 22a and 23a which are 60 stator sleeve 6, and then through the slots 22a and 23a in uniformly distributed peripherally.

51、 The materials from the rings 22 and 23 into an enclosure 36 formed between which are made, firstly, the rings 22 and 23 and, se- said rings 22 and 23 and the annular collar 18. From condly, their supporting structures, in particular the there the air is fed through accelerators 37 borne by said sup

52、porting flange 19 and the supporting peripheral root collar 18 and through the bores 34 in the labyrinth disc 17, are different and have distinctly different coeffici- 65 31 towards the sockets 26a of the turbine rotor disc 26. ents of thermal expansion. Preferably the support struc- The cooling air

53、 path is represented by arrows fin FIG. tures are made of metal and the rings 22 and 23 are made 1. The slots 22a and 23a in the superimposed rings 22 of a ceramic material, which, for example, gives a dif- and 23 are so disposed that in the cold state there is no6 5 4,805,398air passage possible th

54、rough the slots 22a and 23a,intake is thus stopped. No ventilation of the turbine which are completely offset from one another.stator ring is used and no air is bled from the compres- On the other hand, when the temperature rises, thesor. On the other hand, under transient acceleration thermal expan

55、sion of the supports formed by the flangeconditions of the machine, at full throttle, the hot air 19 and the peripheral root 17 and the associated struc- 5 bled from the compressor is fed via thepassages 103b, tures cause the slots 22a and 23a to communicate with143a to the enclosure 142; this results inthermal expan- one another, thus allowing passage of air and hencesion of the meta