US2623688A - Rotary power conversion machine - Google Patents

Description

Dec. 30, 1952 l. M. DAVIDSON 2,623,688

ROTARY POWER CONVERSION MACHINE Filed Dec. 9, 1946 2 SHEETS-SHEET l torneys Dec. 30, 1952 1. M. DAVIDSON 2,623,688

ROTARY POWER CONVERSION MACHINE Filed Dec. 9, 1946 2 SHEETSSHEET 2 FIG. 6

' s2 Mp Mn Mp M g 2r \d Rotor Mn pl 52 3rd Rotor tforney Patented Dec. 30, 1952 UNITED STATES ATENT OFFICE ROTARY POWER: l CONVERSION MACHINE Ivor Macaulay, Davidson, South Farnborough; England, assignor to Power Jets (Research and Development) Limited, London, England, a company of GreatBritain Application-December 9, 1946, Serial No. 715,055 In Great Britain December 13,1945

aclsims. 1:

This. invention relates to improvements in gas eous fluid rotary compressors of the class'in which the dynamic properties of the Workin fluid are utilisedin' order to effect" compression thereof, and one ofits'objectsis to'provide compressor of that class whichis more compact and simple in design and construction thanthe hitherto known compressors for a givenoutput.

Amongst the possible species of compressor of the class referred to, the invention is consid ered to have application to those of the axial flow and radial flow types, even though there maybe a centrifugal componentin" the flow system; but not to those of the pure centrifugalityp'e; Ref erences to a compressor of the kind referred to in the following specification and claims are accordingly, to be read in this limited sense unless the context otherwise requires.

Existing compressors have usually" been designed to operate'by acceleratingthe working fluid and then diffusingit" (i." e. compressing the fluid by deceleration) in orderisubstantiallyfto recover thedynamicpressure thus generated.

This accelerationand diffusion can'be effected,

either in the rotor, or in the stator, or in both;

In existing compressors the Mach number (i. e. theratio of'the velocity-of the fiuidat'any point to the velocity of sound in that fluid at'the same point) is generally less than unity and under these conditions the acceleration of the junction of contiguous zones of flow, at either side of which the fiow velocities are more or less instantaneously changed in such afashion that the velocity components upstream and down-' This phenomenon is represented bya more or less instantaneous change of pressure at stream of and normal tothe. shock, and deter-- mined under localconditions, are respectively supersonic and subsonic (or mother words; the component Mach numbers atthe points in ques' tion are respectively greater and less than unity). It is thus a characteristic ofashock wavethat it can effect compression in-anestremely short distance and with relatively high emciency" the amount of the p essure rise being a measure of the intensity ofthe shock wave.

The present invention is based on the concep tion of utilising this shock wave principle" of energy conversionto obtaiira useful pressure rise in acompressor of the kind referredto. For this purpose, according to the presentinvention'; it is arranged that, in use in the condition of maximum efiiciency, acompression shockwave system of the continuity typeias will be ex plained below) will be set up within the space swept by and will rotate with a compressor rotor in order to utilise the characteristicof rapid conversion of dynamic to pressure energy of such asystem to obtain a pressure rise within that space. The expression compression sh ock wave system used here and in what follows is intendedto mean either a systematic distribution of shock waves or a singly identifiable shock-wave.

view of intensity) will be so contained.

The invention will'be better understood" by, reference to the accompanying, drawings, which include examples of construction in accordance therewith and in which:

Figures 1 and 2 arediagrams illustrating-stile behavior ofa wedge in a gaseous fluid stream ofsupersonic velocity;

Figure 3 illustratesdiagrammatically the'blade arrangement of a possible" form of' axial flow compressoraccording to the invention;

Figures 4 and 5 are vector diagrams corresponding to Figure 3;

Figure 6 illustrates a compound axial new compressor embodying two contra-rotating rotor stages in accordance with the invention and one rotor stage of normal form; and

Figure 7 sets out vector diagrams corresponding to Figure 6.

In order to generate the required shock wave system, the invention, preferably, makes use of the fact that if an obstruction is placed in a fluid stream having supersonic velocity relative thereto (i. e. with a relative Mach number greater than unity) so that the stream is deflected from its original path, a compression shock wave system will be generated, and that if, further, the obstruction is a wedge with one surface parallel to the direction of flow, then only that part of the stream incident on the other surface is deflected and by suitable choice of the included angle of the wedge, it can be arranged that a compression shock wave system is generated on one side only. A shock wave system produced by deflection, for example by a wedge in the manner just described, may conveniently be termed a continuity shock, since it is considered to be the result of an attempted contravention of the principle of the continuity of mass flow, as distinct from what may be described as a momentum shock, which is considered as one due to an attempted contravention of the principle of conservation of momentum. The latter form is exemplified in the behaviour of a supersonic flow in an overexpanding de Laval nozzle; in such a nozzle, if there were no losses and the fluid were a perfect gas, expansion would take place until the Mach number became infinite and the temperature infinitesimal, but in practice these conditions cannot be satisfied so that a shock wave must be formed in the nozzle if the law of conservation of momentum is to be obeyed.

Reliance upon a momentum shock wave system as the pressure-raising shock system called for by the invention within the space swept by the rotor would be a practicable alternative to the use of a continuity shock system, since the former system could be made to operate efliciently and could be produced by arranging for the flow through the rotor blading to be supersonic and shaping the blades to simulate an overexpanding de Laval nozzle. Although in such a case, given an inlet Mach number of not less than unity, some sort of continuity shock wave would necessarily be generated at the leading edges of the blades (since these must have a finite thickness), such a shock wave would not necessarily be propagated so as to be contained within the space swept by and to rotate with the rotor, in which case from the point of view of obtaining useful pressure rise for the purpose of the present invention, the momentum shock wave system within the blade passages could be regarded as operating alone. It is thought, however, that an arrangement using a momentum shock system alone in this way would possess inferior aerodynamic stability and width of operating range as compared with one relying upon a continuity shock to provide the pressure raising shock system called for, and that for fully effective operation such a momentum shock system would require to be stabilised by the formation of a continuity shock system upstream thereof and within the space swept by the rotor.

Accordingly (but without prejudice to the generality of the appended claims) the invention in its present preferred form contemplates in the first place, that the shock wave system should be generated at the rotor inlet by reason of deflection by the rotor blading of a flow which is super- .4 sonic relative thereto, and, as a further feature, that the leading edge of this blading should constitute a wedge (which requirement for the purpose of this specification is to be taken to be satisfied if the faces of a blade intersect to form a well defined edge at which planes tangential to the faces of a blade define a wedge shape). Preferably said leading edge is knife-edged, whilst in order to ensure the desired preponderance of shock intensity within the space swept by the rotor it is arranged that the major deflection of flow is by the leading face of a blade, the rear face being arranged (ideally) parallel with the incident relative fluid flow, or at least more nearly parallel therewith (before deflection) than is the leading face.

Some degree of choice is possible in the selection of the wedge thickness, but to give the best results the included angle of the wedge, for a given incident Mach number, should be less than what will be termed herein the detachment angle. The explanation of this term is as follows:

If, as illustrated in Figure 1 of the accompanying drawings, a relatively thin wedge 4 is placed in a supersonic stream F the resultant shock wave W will be seated on the wedge apex and (if the incident relative flow is parallel with one of the faces) at one side only thereof, as illustrated, but if, for a given Mach number of the incident flow, the included angle 6 be increased there will be reached a value at which the shock wave moves a short distance upstream, as illustrated in Figure 2, and is thus completely detached from the wedge as well as being propagated at both sides thereof. It is this value of the included wedge angle that for a given incident Mach number is considered herein to be the detachment angle of the wedge at that Mach number.

The formation of a continuity shock wave system as described in the foregoing, of course, necessarily involves a Mach number of the fluid relative to the rotor at inlet thereto of not less than unity; preferably, however, the Mach number at this point, considering the velocity of the fluid alone (i. e. relative to a stator element), is less than unity. Similarly it is desirable that the Mach number of the fluid relative to the rotor at outlet therefrom should be less than unity, although adequate results should be obtainable even if there are local zones of supersonic velocity at the rotor outlet. In general, if the fluid velocities relative to the rotor only are permitted to become supersonic, as is the case in the ideal form of this invention, higher efficiencies will result than those otherwise obtainable with supersonic compression.

A system according to the invention as applied to one axial flow compressor stage and relying upon a continuity shock wave system for obtaining pressure is illustrated diagrammatically in Figure 3 of the accompanying drawings in which a rotor element 2, of which 2A, 2B are two adjacent blades, rotates in the direction shown by the arrow and is disposed between an inlet stator element l and an outlet stator element 3. It will be understood that the rotor and stator elements fragmentarily illustrated in Figure 3 are parts of complete circular bodies which are coaxial and bladed around their entire peripheries. The symbols used in the corresponding vector diagrams appearing as Figures 4 nd 5 have the following meanings:

M-Mach number -air angle, measured from the axial direction and thesubscripts have thefollowing meanings: p--periphera l r-relative to rotor s--r elative to an adjacent stage of stator or other bladin in guide blade relationship with the rotor being considered 1'-stator (or guide blade) outlet and rotor inlet 2-rotor outlet and stator inlet The diagram in Figure 4 shows the Mach numbers Mn and M51 of the working fluid at. entrance to the rotor element, relative to the rotor and stator elements respectively.

Figure 5 shows the corresponding Mach numbers at therotor outlet, i. e. Mrz and M52,

The conditions envisaged are:

(i) That, the Mach number relative to the rotor at inlet to the rotor (Mn) must be not less than, unity, whilst that at outlet from the inlet stator l (M51) should be less than unity. As will be evident to those skilled in the art these conditions can be satisfied by; applying normal considerations of compressor design in respect of blade stagger angles, air inlet and outlet angles and relative velocities, according to design requirements, to give vector diagrams such as those illustrated. It will be evident that the desired low value of M51 and high value of Mn can best be attained by making the vectors M51, Mp1 arithmetically additive, implying the arrangement of the blades of the stator l and rotor 2, as illustrated, with their stagger (inclination to the foreand-a ft line). in the same sense as each other and the direction of;rotation,of the rotor;

(ii) Thatthe leading edge. of each rotor blade should constitute a Wedge as hereinbefore defined (preferably knife-edged) whose included angle is not greater; than the detachment angle for the incident Mach number in the design conditionsof operation;

(iii) That ideally the angle of incidence of the fluid on the rotor blades should be so related to the. disposition of the blade faces on the basis of the principlesalready explained that the compression shock wave system is generated only at the leadingface of each blade, so .that compression shock waves are not propagated into the upstream stator element; or at least thatthe intensityof the shockwave system at the leading faceof a blade should be. greater than that at the. rear face; further, that. the shock wave generated at the leading face of a blade should be'confmed to the rotor space by the rear face of the preceding blade.

The ideal arrangement contemplated might, forexample, be such that a compression shock wave PQ from arotor blade 25 is reflected one or more. times (as indicated by QR) at the underside of the next rotor blade 2A in the series.

In a. non-ideal, but nevertheless useful system, theremight, however, bea compression shock wave ES of less intensity than PQ which, due to its direction at the rear of the blade 2B, might be propagated into the upstream stator element I.

In order to obtain a large pressure rise from the compressorstage under consideration it is desirable that the relative outlet Mach number from therotor (Mrz) should be less than unity. Thejblading might well be designed, however, for a shock wave system within the space swept by the rotor such as would result in supersonic velocities atsome zone of the outlet, without unacceptably impairing the effectiveness of the compressor. In any event the inlet Mach num her at the stator} shouldbe less; than unity, a

6. condition which can best be satisfied by making the vectors Mp2, Mrz, arithmetically subtractive as illustrated, the inlet angle of the stator 3 being selected to conform to theresultant in accordance with usual practice. of the stator 3 will follow normal practice, and depend on the duty it is to perform and theair outletangle required.

As the fluid velocities relative to the rotor are,

high it is desirable, if large losses are. to be avoided, that as well as the provision of a. leading edge of wedge form having an appropriate included angle, unnecessarily high curvatures should be avoided in the design of the rotor blade.

profiles. For this purpose one form of rotor blade may. conveniently be that shown, in Figure 3, namely, a lei-convex profile having very little; camber, but other profiles, for example, concavo-- convex or double wedge i. e. rhombic, having little or no camber, could also be employed.

It will be understood that the compressor should be designed so that the shock wave system in the space swept by the rotor will be main tained throughout the intended useful operating range of the machine (i, e. throughout this range the value M should be not less than,

unity) 'lhe main advantages ofa compressor of the,

type described are that whilst orieringthe possibility of achieving simplicity and lightness comparable with that of a centrifugal unit it also has the superior form of the axial flow compressor. Two, or more compressor stages according to the invention may be compounded comparatively easily, thus making; high pressure ratio,

practicable in a single compact machine, or one or more such stages may be compounded with stages (including centrifugal stages) not in accordance with the invention. Since the working fluid is deflected through a large angle, compounding might well be effected by the provision of a contra-rotating unit without the use of intermediate stator blading. For this purpose it would merely be necessary to arrangethe blade inlet angles of each successive, contra-rotating tionary or rotating in guide blade relationship. therewith) of a possible compounded arrangement embodying-a stator I and rotor 2 having blades 2a as already described with reference to Figure 3, and a similar contra-rotating second stage rotor 55 having blades 5A with an inlet Mach number of not less than'unity, followed by a stator These might be followed by arotor 6 designed for normal subsonic operation (inlet Mach number less than unity) and a corresponding outlet stator 1.

The system according to the invention is par-- ticularly suited for use in aircraft gas turbine engines, but is not of course limited to this application.

It might be thought that the end sought to be achieved could be obtained by the (use of a com.-

The remaining design.

pression shock system in a stator part downstream of the rotor, but it would be found that such an arrangement would involve a large defiection of the fiow by the rotor and stator blading and would result in very inefficient operation. For this reason the utilisation of a compression shock system in the space swept by the rotor is regarded as an essential feature of the invention.

I claim:

1. A gaseous fluid rotary compressor comprising a rotor and an annulus of rotor blades peripherally attached thereto, said blades defining between them passages for the flow of gaseous fluid to be compressed, each rotor blade being inclined to the axial plane of the rotor and the leading edge being in advance of the trailing edge with respect to the direction of rotation of the rotor, the leading portion of each rotor blade having forward and rear apical faces defining a wedge, an annulus of stator blades immediately upstream of said rotor blades, each stator blade being inclined in the same general direction as the rotor blades, said stator blades being so contoured, oriented, and spaced that in cooperation with the rotor at the design operating speed of the latter for the particular fluid to be compressed the resultant incident flow of gaseous fluid relative to the rotor blades is substantially aligned. with the apical face at the rear of the leading portion of said rotor blades, the forward apical face of said leading portion of the rotor blades being inclined to said resultant incident flow for efiecting a compression shock wave of the continuity type in the passages between the rotor blades at supersonic velocities of said resultant incident flow relative to said rotor blades.

2. A gaseous fluid rotary compressor comprising a rotor and an annulus of rotor blades peripherally attached thereto, said blades defining between them passages for the flow of gaseous fluid to be compressed, each said rotor blade being inclined to the axial plane of the rotor and the leading edge being in advance of the trailing edge with respect to the direction of rotation of the rotor, the leading portion of each rotor blade having forward and rear apical faces defining a wedge, an annulus of stator blades immediately upstream of said rotor blades, each stator blade being inclined in the same general direction as the rotor blades, said stator blades being so contoured, oriented, and spaced, that in cooperation with the rotor at the design operating speed of the latter for the particular fluid to be compressed, the resultant incident flow of gaseous fluid relative to the rotor blades is substantially aligned with the apical face at the rear of the leading portion of said rotor blades, the forward apical face of said leading portion of the rotor blades being inclined to said resultant incident flow for effecting a compression shock wave of the continuity type in the passage bounded by the forward face of said rotor blade and the rear face of the next preceding rotor blade at supersonic velocities of said incident flow and said compression shock wave being confined within said passage by the rear face of said next preceding rotor blade.

3. A gaseous fluid rotary compressor comprising a first rotor and a first annulus of rotor blades peripherally attached thereto, a second rotor coaxial with and adapted to rotate in the opposite direction to said first rotor and a second annulus of rotor blades peripherally attached thereto and lying immediately downstream of said first annulus; the blades of each said an nulus defining between them passages for the flow of gaseous fluid to be compressed; each said blade of said second annulus being inclined to the axial plane of the rotors and the leading edge being in advance of the trailing edge with respect to the direction of rotation of said second rotor; the leading portion of each blade of said second annulus having forward and rear apical faces defining a wedge, each said blade of said first annulus being inclined to the axial plane of the rotors and the leading edge being in advance of the trailing edge with respect to the direction of rotation of said first rotor, said first annulus of rotor blades being so contoured, oriented and spaced that in cooperation with the second rotor at the design operating speed of said rotors for the particular fluid to be compressed, the resultant incident flow of gaseous fluid relative to said second annulus of rotor blades is substantially aligned with the apical face at the rear of the leading portion of said rotor blades of the second annulus, the forward apical face of the leading portion of the rotor blades of said second annulus being inclined to said resultant incident flow for effecting a compression shock wave of the continuity type in the passages between the rotor blades of the second annulus at supersonic velocities of said incident flow.

e. A gaseous fluid rotary compressor comprising a first rotor and a first annulus of rotor blades peripherally attached thereto; a second rotor coaxial with and adapted to rotate in the opposite direction to said first rotor and a second annulus of rotor blades peripherally attached thereto and lying immediately downstream of said first annulus; the blades of each said annulus defining between them passages for the flow of gaseous fluid to be compressed; each said blade of said second annulus being inclined to the axial plane of the rotors and the leading edgeibeing in advance of the trailing edge with respect to the direction of rotation of said second rotor, the leading portion of each blade of said second annulus having forward and rear apical faces defining a wedge, each said blade of said first annulus being inclined to the axial plane of the rotors and the leading edge being in advance of the trailing edge with respect to the direction of rotation of said first rotor; said first annulus of rotor blades being so contoured, oriented and spaced that in cooperation with the second rotor at the design operating speed of said rotors for the particular fluid to be compressed, the resultant incident flow of gaseous fluid relative to said second annulus of rotor blades is substantially aligned with the apical face at the rear of the.

leading portion of said rotor blades of the second annulus, the forward apical face of the leading portion of the rotor blades of said second annulus being inclined to said resultant incident flow for effecting a compression shock wave of the continuity type in the passage bounded by the forward face of said rotor blade of the second annulus and the rear face of the next preceding rotor blade of the second annulus at supersonic velocities of said incident flow and said compression shock wave being confined within said passage by the rear face of said next preceding rotor blade of the second annulus.

IVOR MACAULAY DAVIDSON.

(References on following page) 9" 10 REFERENCES CITED FOREIGN PATENTS The following references are of record in the Number Country Date file of this patent: 417,170 Great Britain Sept. 2-8, 1934 479,427 Great Britain Jan. 31, 1938 UNITED STATES PATENTS OTHER REFERENCES Number Name Date 1,518,501 G111 Dec. 9, 192 Flight Magazine, page 450, Nov. 4, 1937, article ,571 Bothezat June 11, 1935 by C. N. Lock (U. S. P. 0. Library book No. TL, 2,201,099 Roe May 1 1 501, .F 775). 2,219,937 ama fi Oct. 29, 1940 10 Article by A. Ferri (Atti di Guidonia, No. 37-38, 2,224,519 McIntyre Dec. 1 194 pages 517-557) Oct. 11, 1940 (U. S. P; 0. Library 2,378,372 Whittle June 12, 1 book No. TL, 565, .F4). 2,426,270 Howell Aug. 26, 1947 2,435,236 Bedding Feb. 3, 1948

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