OPERATING CYCLES FOR TURBOCOMPOUNDED TWO-STROKE PISTON ENGINES

Abstract: An operating cycle for a turbocompounded 2-stroke piston engine comprises a compression stroke, shown as B-A-G on the indicator diagram and an expansion stroke G-K-L-B. The expansion stroke expands the combustion gases to a pressure PB which is lower than the turbocharging pressure PA, scavenging of the combustion gases from the piston engine being facilitated by purging the piston engine with turbocharging air during an early part B-A of each compression stroke B-A-G. This causes the compression ratio RA of the piston engine to be substantially less (preferably, about half) of its expansion ratio RB. Among other advantages, the cycle enables better scavenging of combustion products from the cylinders, and enables the piston engine to be better matched to the associated turbine/turbocompressor set, which may be a gas turbine engine.

Description: 1 OPERATING CYCLES FOR TURBOCOMPOUNDED TWO-STROKE PISTON ENGINES This invention relates to improved operating cycles for turbocompounded 2-stro e piston engines. By the term "turbocompounded 2-stroke piston engines" is meant a 2-stroke reciprocating piston engine adapted to be linked to a turbine-turbocompressor set so that the exhaust gases of the former drive, or help to drive, the turbine of the latter, which drives the turbocompressor, which in turn turbocharges the piston engine. The turbine/turbocompressor set may be part of a gas turbine engine capable of operating independently of the piston engine, or may operate merely as a turbocharger. It has long been considered desirable to turbocharge piston engines operating on a 2-stroke cycle in order to maximise power output and fuel efficiency while minimising specific weight of the engine. A good early example of this type of engine as applied to aircraft propulsion was the "Napier Nomad", described for example, in the magazine "Flight", vol. 65, no. 4, April 1954, pp. 543-551. It consisted of a turbocharged 12-cylinder, 2-stroke diesel with the turbine/turbocompressor set driven off the diesel's exhaust, the two parts of the engine being inter¬ connected through a variable gear which allowed the two shaft speeds to be optimally matched over the flight regime of the aircraft in which it was installed. It was not commercially successful, apparently because it was heavier and more complex than equivalent turbojets; also, turbojets offered higher speeds, while fuel at the time was relatively cheap so that the higher fuel consumption of the turbojet was not very much of a penalty. More recently, U.S. Patent NO. 4449370 discloses a compound engine for aircraft use in which a low compression turbocharged diesel engine has a turbocharger which can be operated independently of the diesel. This is possible because although the turbine receives the exhaust gases from the diesel, they first pass through a catalytic combustor inserted in the cycle before the turbine, so that whenever needed, fuel and air can be supplied to the catalytic combustor to provide additional heating of the exhaust gases; furthermore, a valve and ducting is provided so that the diesel engine can be selectively bypassed, the compressor (blower) air being passed straight to the catalytic combustion chamber to drive the turbine and hence provide power for auxiliary equipment during the starting sequence. A survey of these and other proposed examples of turbocompounded 2-stroke piston engines seems to reveal that, though of varied type and construction, they follow convention for such engines in that the pressure at which the turbocharging air is delivered to the piston engine is lower than the pressure at which the combustion gases from the piston engine are exhausted to the turbine. Furthermore, considering examples of 2-stroke piston engine operating cycles in the ordinary case where they are not turbocompounded, it can be observed that, as a general rule, their compression ratios are approximately the same as their expansion ratios. It appears to be a fact that this general rule has also been applied to them when they have been compounded with turbine/turbocompressor sets. It is here contended that the facts mentioned in the above two paragraphs are disadvantageous because, for reasons which will be appreciated later, they result in the overall operating cycles of turbocompounded 2-stroke piston engines being less efficient and powerful than they could be. It is an object of the present invention to " provide operating cycles for turbocompounded 2-stroke piston engines which enable them to be more efficient and/or powerful than hitherto. Accordingly, the present invention provides an operating cycle for a turbocompounded 2-stroke piston engine, said 2-stroke piston engine being adapted to be linked to a turbine/turbocompressor set so that combustion exhaust gases from the piston engine at least partly drive the turbine, which drives the turbocompressor, which in turn turbocharges the piston engine; said operating cycle comprising a compression stroke and an expansion stroke, the expansion stroke expanding, the combustion gases to a pressure lower than the turbocharging pressure, scavenging of the combustion gases from the piston engine being facilitated by purging the piston engine with turbocharging air during an early part of each compression stroke, whereby the piston engine has a compression ratio which is substantially less than its expansion ratio. Among other advantages, this cycle assures good scavenging of spent combustion products from the piston engine; at the same time a good match is obtained between the compression and expansion characteristics of the turbine/turbocompressor set and the piston engine. Preferably, the compression ratio of the piston engine is approximately half its expansion ratio: preferably the compression ratio is half the expansion ratio, plus 0.1. The value of the expansion ratio of the positive displacement engine may be in the range 3 to 12 inclusive. For operation at sea level and normal land altitudes, the expansion ratio is preferably in the range 3 to 8 inclusive, while for operation at high altitudes a range of 6 to 12 inclusive is preferred. The turbine/turbocompressor set is provided with pressure ratios concomitant with these expansion ratios of the positive displacement engine. A further aspect of the invention calls for the piston engine to be turbocharged with turbocharging air during an early section of the compression part of the cycle and the turbocharging air is compressed during a last section of the compression part of the cycle, scavenging of combustion gases from the piston engine being aided by purging with turbocharging air during at least an initial portion of said early section of said compression part of the cycle. It should be understood that the turbines and the turbocompressors mentioned above may be either of the radial flow type or of the axial flow type, according to which type can be made to perform their part of the overall operating cycle most efficiently. A leading advantage of the concepts outlined above is that they provide a means of greatly increasing the air flow through a given size of 2-stroke piston engine - and hence the power produced - without necessarily generating high peak combustion pressures in the cylinders. Furthermore, the air charge can be made cleaner before combustion occurs than in prior- such engines. The concepts are very suitable for use where the 2-stroke piston engine is a diesel engine, but could also be applied to both spark ignition engines and those fueled by gas. Embodiments of the invention will now be described, by way of example only, with reference to the accompanying drawings, in which:- Figure 1 is a schematic diagram of a compound engine comprising a gas turbine engine linked to a 2-stroke reciprocating piston engine; Figure 2 is an indicator diagram showing the operational cycle of the piston engine of Figure 1; Figure 3 is an indicator diagram like that of Figure 2, but additionally showing possible ranges of compression and expansion ratios for the piston engine of Figure 1; 5 Figure 4 is a schematic cross-sectional side elevation of a cylinder head configuration suitable for a 2-stroke piston engine performing the cycle shown in Figure 2; Figure 5 is a view on section line V - V in Figure 4; Figures 6(a) to 9(a) are views similar to Figure 4 but showing the cylinder at successive stages in the scavenge and induction section of the cycle shown in Figure 2; Figures 6(b) to 9(b) are timing diagrams for the 2-stroke cycle at the successive stages of the cycle shown in corresponding Figures 6(a) to 9(a); Figures 10(a) and 10(b) are diagrammatic cross- sectional elevations of an inlet valve arrangement alternative to that shown in Figure 4, for use with engines having large expansion ratios; Figure 11 is a schematic cross-sectional side elevation of another alternative cylinder configuration similar to that of Figure 4, but also incorporating- the essential features of Figure 10; Figure 12 is a view on section line XII - XII in Figure 11; Figures 13(a) to 16(a) are schematic cross- sectional side elevations of a further alternative cylinder configuration suitable for an engine performing the cycle shown in Figure 2, the cylinder being shown at successive stages in the scavenge and induction section of the cycle; and Figures 13(b) to 16(b) are timing diagrams for the cycle at the successive stages shown in corresponding Figures 13(a) to 16(a). Referring now to Figure 1, there is shown, in schematic form, a compound engine comprising a multi-cylinder 2-stroke diesel engine 100 compounded with an atmospherically aspirated, twin spool, axial flow gas turbine engine 102 which is shown partly in axial cross-section. Both the diesel engine 100 and the gas turbine engine 102 may be derived from known types, but modified to the extent necessary to work the invention. As is normal, the pistons (not shown) are connected to a crankshaft (not shown) which drives a low speed output shaft 104. As will be explained later, the two engines are compounded together in such a way that their individual thermodynamic cycles are efficiently matched. it will be seen from Figure 1 that the turbocompounded diesel engine 100 is aspirated by turbocharging it from the output of the turbocompressor 106 of the gas turbine engine 102 through a turbocharger ■ air duct 108. This air duct 108 incorporates an air valve 109 by means of which the air duct can be partially or completely obturated when required, as explained later, so as to reduce or prevent aspiration of the diesel engine 100. In fact, the turbocharging air in air duct 108 is split two ways, one way being through a branch duct 110 for use as cooling air for cooling the cylinder head, cylinder liner and other components of the diesel engine 100, and the other way being through a continuation of duct 108 to aspirate the cylinders. In order to adjust the temperature of the turbocharging air to an optimal value for making the diesel engine semi-adiabatic, it is probably necessary to incorporate a heat exchanger 112 in duct 108. If cooling of the turbocharging air is required, the fluid with which the air exchanges heat could be the fuel supply to the gas turbine engine 102 and/or the diesel engine 100, or heat could be rejected to the atmosphere through a fan-assisted radiator. If warming of the turbocharging air is required, the heat exchange fluid could be exhaust air from the cooling system(s) of the diesel engine 100 and/or the gas turbine engine 102. A beneficial effect of using turbocharging air to cool the cylinder components is that the extraction of heat (up to 30% of total heat liberated) means that less fuel is required in the gas turbine engine's combustion chamber. The gas turbine engine can therefore generate power at a significantly improved fuel consumption, which could be similar to that of the diesel. The fuel consumption of the combined unit is thereby improved. In addition to the heat exchanger 112, the turbocharging air supply duct 108 preferably includes a scavenge pump 114 in the form of a low pressure-ratio supercharger of known type which can be driven from the electrical system (not shown) of the compound engine, or preferably by a mechanical power offtake (not shown) from the diesel engine 100 or the gas turbine engine 102. The scavenge pump 114 may well be necessary in order to promote turbocharging air flow into and through the diesel engine 100 as required by the invention since the pressure difference between the outlet of the turbocompressor 106 and the exhaust outlet of the diesel engine may otherwise be insufficient to cause adequate circulation of the air through the cylinders and the cooling system. Instead of being used for turbocharging, some (or if valve 109 is closed, all) of the air from the turbo¬ compressor 106 is delivered directly to an annular combustion chamber 116 of the gas turbine engine 102, fuel being injected into the combustion chamber in known way by fuel injector nozzle 118 for burning with the turbocompressor delivery air. With air valve 109 partly or completely open, combustion occurs not only with the air from turbocompressor 106, but also with exhaust cooling air from the diesel's cooling system and with exhaust combustion gases from the diesel's exhaust ports. Although air valve 109 is thought to be a necessary component of the compound engine for most purposes for which such an engine would be used, it would of course be preferably to do without it if possible for the sake of simplicity. This would depend upon the practicalities of the design in each case; for 5 example, whether the diesel and gas turbine engines and their accessories were of such a design that both engines could be started simultaneously. During design of the compound engine, it should also be considered whether the air valve 109, if 10 present, should be progressive in its opening and closing action, as specified above, or alternatively be a simple two-position open/close valve. This choice will depend upon whether throttling of the turbocharging air supply to the diesel engine 100 is desirable during 15 an part of its operating range. Having exited the diesel engine 100 the exhaust cooli ' ng air and the exhaust combustion gases are conveyed to the gas turbine engine 102 by means of respective exhaust ducts 120 and 122. To ensure even •20 distribution of both types of diesel exhaust around the annular combustion chamber 116, the exhaust ducts 120 and 122 discharge into respective annular distribution ducts 124,126 which surround the combustion chamber. From distribution duct 124, the diesel exhaust cooling 25 air is passed through a number of equi-angularly spaced-apart distribution ports 128 to the region immediately surrounding the upstream end of the combustion chamber 116 so that it can gradually pass into the combustion chamber through air dilution holes 30 (not shown) in the chamber wall, as known, to take part in the combustion process at a slightly later stage than the air coming direct from the outlet of the compressor 106. The diesel exhaust combustion gases in distribution duct 126, however, are passed through 35 distribution ports 130 direct to a downstream interior region of the combustion chamber 116 so as to join the combustion process at a still later stage. After passing through nozzle guide vane ring 132, the combustion gases exiting the gas turbine engine combustor 116 are expanded through a high pressure turbine 134, which extracts sufficient energy from the combustion gases to drive the turbocompressor 106, this being mounted on the same drive shaft 136 as the high pressure turbine. Finally, the gases are expanded through a free power turbine 138 to atmosphere. This is mounted on an output shaft 140 which runs inside shaft 136 and takes the output power to the forward end of the gas turbine engine 102. Taking an overall view of the compound engine shown in Figure 1, the power outputs comprise a low speed output shaft 104 from the diesel engine 100, and a high speed output shaft 140 from the gas turbine engine 102. Mechanical, fluid or electrical coupling together of the two shafts may or may not be desirable, depending upon the power developed by the engines and the uses to which the power may be put. Such mechanical, fluid or electrical coupling is of course known in the art and so will not be described here in detail. For example, in high power aeroengine applications, the powers developed may be too great for easy handling by gears or fluid couplings, so that it may be advantageous to use the output shaft 104 to drive a large relatively slow turning propeller or ducted fan, while using the output shaft 140 to drive a smaller relatively fast turning propeller or ducted fan. In contrast, for a helicopter engine arrangement, the two output shafts 104,140 could be geared together to drive the main rotor through a modified form of helicopter reduction gear. Starting of the two engines 100,102 relies on known technology. Thus, the gas turbine engine 102 could be started using a known type of electrical or air starter. If the diesel engine shaft 104 is not coupled to the gas turbine engine shaft 140, it would be necessary to utilise a conventional form of electrical or air starter motor for starting the diesel engine 100. A suggested starting and operational sequence for the compound engine of Figure 1 is as follows:- (a) The gas turbine engine 102 is started first and is run up to a suitable idling speed as an independent unit, the air valve 109 being closed, so that there is no air feed to the diesel engine 100. (b) When the gas turbine engine 102 is self-sustaining and is developing some power, the diesel engine 100 is then started, using either a separate starter motor attached to shaft 104, or by driving it through a coupling between shafts 104 and 140. The air valve 109 is opened, scavenge pump 114 is started, and fuel is admitted to the diesel engine. (c) As the diesel engine 100 accelerates into its normal running range, both the gas turbine engine 102 and the diesel engine continue running as separately fueled units while cooperating synergistically as a compound engine, the gas turbine engine turbocharging the diesel engine and the diesel engine exhaust contributing to the power being developed by the gas turbine engine. (d) During operation the amounts of power developed by each engine can be varied relative to each other to give optimum performance or efficiency. Since the supercharged diesel engine will be more fuel efficient than the gas turbine engine, it will, if possible, be advantageous to arrange that for periods when the total power output required from the compound engine is steady at moderate or low levels, most of the power is supplied by the diesel engine component, the gas turbine engine being throttled back or extinguished: in the latter case, it would function as a turbocharger but with some power produced by the power turbine. However, higher power levels could easily be supplied by arranging for the gas turbine engine to operate lit at a higher power level and thus supply a greater proportion of the total power of the compound engine. It should be noted that the gas turbine engine 102 is preferably designed to operate at a high pressure ratio. Hence operation of the compound engine with the gas turbine engine lit, rather than operating unlit as a turbocharger, would not involve excessive fuel consumption. The arrangement shown in Figure 1 is capable of as much variation in design as other forms of turbocompounded unit and features such as further heat exchangers, re-generation and bottoming cycles could be included. Referring now to Figure 2, there is shown an idealised indicator diagram expressive of the overall operating cycle of the compound engine discussed in relation to Figure 1, in which air and combustion gas pressures in pounds per square inch absolute are plotted as the ordinate against the corresponding volume ratios of the diesel engine and the gas turbine engine at various stages in the cycle. The overall cycle may be described as follows:- (i) Air at atmospheric pressure enters the turbocompressor 106 (Figure 1) at point J and is delivered as turbocharging air to the cylinders of the diesel engine 100 at point A with a turbocharging pressure P . Point A is a point during the first or compression stroke of the preferred 2-stroke cycle, after bottom dead centre. (ϋ) Between points A and G the charge of air in the cylinder of the diesel engine is compressed as the piston travels up the cylinder towards top dead centre. (iii) Combustion occurs at approximately constant volume between points G and K, and at approximately constant pressure between K and L. (iv) From L to B -expansion occurs in the cylinder as the piston travels back down the cylinder towards bottom dead centre at B, whereupon the combustion gases from the diesel are exhausted at a pressure P_ o to the turbine of the gas turbine engine and expansion is continued in the turbine back down to near atmospheric pressure at point M, which represents exhaust from the gas turbine engine. (v) The sloping line B to A should be particularly noted, since in effect this represents the process of scavenging the spent combustion gases from the cylinder and the "induction" of the new σharge of turbocharging air for compression in the next cycle " , i.e. line BA indicates that "scavenging" and "induction" in the diesel engine must take place as the pistons move upwards from bottom dead centre during a first section of their compression strokes. Further features of the compound engine of Figure 1 will now be explained with reference to Figure 2. Firstly, the turbocharging air in duct 108 is delivered to the cylinders of the diesel engine 100 at a pressure P which is higher than the pressure P„ at which the combustion gases from the cylinders are exhausted to the turbine 134 through duct Ϊ22. As mentioned previously, this pressure drop across the diesel engine 100 helps promote adequate circulation of the turbocharging air through the cylinders of the diesel and may be ensured by incorporation of scavenge pump 114 in air duct 108. A further advantage is that because P is not any less than P B , explosive decompression does not occur when the inlet valves open. Previous practice of making P less than P β has led to such decompression, resulting in unwanted mixing of the spent combustion gases with the new incoming air charge. p Secondly, the compression ratio A of the diesel engine 100 is substantially less than its expansion ratio R B , R being approximately half the value of R-,. In fact the ideal theoretical relationship would appear to be R A z- 0.5.R β + 0.1. 13 Thirdly, the fact that overall the complete indicator diagram in Figure 2 is divided by the sloping line A-B, indicates good matching between the compression and expansion characteristics of the diesel engine 100 and the gas turbine 102 in that though the lower part of the diagram J-A-B-M is a typical gas turbine engine indicator diagram, the upper part A-G-K-L-B-A for the diesel engine breaks with convention in not having compression and expansion ratios approximately equal, i.e. its cycle has been altered to make it a better match for the gas turbine engine. An advantage of this almost horizontal division of the complete indicator diagram by the sloping line A-B is the design flexibility which it gives regarding the size relationship between the diesel engine and the gas turbine engine. Referring to Figure 3, it will be seen that the sloping line A-B can be drawn at any level of turbocharging pressure without effecting either the theoretical area of the indicator diagram or the peak cylinder pressure, the compression and expansion ratios of the diesel engine bearing the same proportionate relationship to each other no matter what turbocharging pressure is adopted. Hence, as the line A-B moves upwards on the diagram, the size of diesel engine required to handle any given air flow through it is reduced, because the compression and expansion ratios of the diesel engine are reduced. It should be noted that power output from the diesel engine is a function of the pressure ratio of the turbocompressor - doubling the pressure ratio increases the power output by approximately two-thirds as much again - because the power produced in each cylinder depends mainly upon the mass of air contained in the cylinder clearance volume at top dead centre. Looking at Figure 2, the compression ratio R ft is defined as the volume V of the cylinder swept by the piston plus the unswept or 14 clearance volume v of the cylinder, divided by the clearance volume, i.e. R A = (v + V) /V, therefore v = V/(R A - 1) , hence as the compression ratio is reduced to low values, the cylinder clearance volume becomes large. This relationship can be used advantageously by low compression ' ratio designs in accordance with our invention because use of a high pressure ratio turbocompressor enables the pressure and temperature of the air retained in the cylinder at the top of the compression stroke to be at normal diesel values, even though large air mass flows are being processed and high powers produced. Alternatively, even higher powers are obtainable if use of advanced heat resistant materials in the pistons and cylinder head, such as superalloys and high-strength ceramics, allows increases in peak cylinder pressure and temperature. In these ways, more of the compression and expansion is carried but in the gas turbine engine and correspondingly less in the diesel engine. Figure 3 gives some indication of likely practicable overall ranges for compression and expansion ratios of the 2-stroke diesel of Figure 1. Overall, the value of the expansion ratio is unlikely to be outside the range 3 to 12 inclusive, and for operation at sea level and normal land altitudes a preferred range for expansion ratio would be 3 to 8 inclusive. At high altitudes (say,20,000 to 40,000 feet, the compound engine being a powerplant in a transport aircraft) a preferred range for expansion ratio would be 6 to 12 inclusive. Although these ranges are preferred as practicable design parameters for the diesel engine and the gas turbine engine with which it is compounded (the pressure ratios of the turbocompressor and turbine being chosen to match the compression ratio and expansion ratio of the diesel engine as mentioned previously) , the advantages of giving the diesel engine as low a compression ratio as possible should be borne in mind. It should be noted . that the diesel engine could incorporate a variable compression ratio cylinder head. This would be capable of varying the compression ratio by approximately 50%. Turning now to Figures 4 and 5, there is shown, respectively, a cross-sectional side elevation and a view on section line V - V of part of a cylinder 400 with a cylinder head configuration which can be incorporated in piston engine 100 of Figure 1 and which is particularly suited to the proposed 2-stroke cycle of the invention. The cylinder head 401 incorporates an indirect combustion chamber 402 which is provided with a heater 404 (known in itself) for aiding combustion and a fuel injector 406, the latter component being conventional and indicated only by an arrow. Indirect combustion chambers, swirl chambers or atomisers are already used in a wide variety of reciprocating piston engines, but use is confined to the smaller sizes of engine. Advantages ascribed to the use of indirect combustion chambers are the ability to use higher fuel/air ratios, the ability to use simple "single-hole" fuel injectors, the ability to use fuels having poor ignition characteristics, and the ability to utilise high peak combustion pressures. The penalty set against these advantages is an increase in pumping losses. However, when an indirect combustion chamber configuration is utilised in conjunction with the proposed 2-stroke cycle, certain further advantages can be made to accrue. These are connected with the fact that according to the cycle, the combustion gases are exhausted from the cylinders to the turbine at a lower pressure than that at which the turbocharging air is delivered to the cylinders, and that the compression ratio of the cylinders is preferably about half the expansion ratio. As previously noted with respect to Figure 2, this makes the 2-stroke piston engine cycle a good fit on top of that of a high pressure ratio turbine/turbocompressor set such as might be derived from an aero-type gas turbine engine, and enables the expansion ratio, but particularly the compression ratio, of the piston engine to be minimised. This enables the indirect combustion chamber to be made large enough, as in Figures 4 and 5, for a large diameter inlet valve 408 to be fitted to it, the remainder of the cylinder head area being used for exhaust valves 410 to provide a large valve area. This is advantageous in maximising the mass flow rates of turbocharging air and combustion gases through the cylinders and hence increasing the power. Again, it will be understood by the person skilled in the art that because the proposed cycle minimises the compression- ratio of the piston engine, a smaller volume of turbocharging air is introduced into the cylinder before compression as such commences, i.e. the fresh charge of air at turbocharging pressure only occupies a fraction of the total volume of the cylinder. In the prior art, however, the compression and expansion ratios are more nearly equal and the cylinder must therefore be completely filled with turbocharging air. Since the incoming air charge is partly used to scavenge the combustion gases from the cylinder, it will be apparent that the proposed cycle might well be used to minimise wastage of turbocharging air in the scavenging process, and the configuration shown in Figures 4 and 5 helps to realise this possibility. Thus, the fact that the cycle enables the inlet valve 408 to be incorporated in a large indirect combustion chamber 402, allows the passage 412, which connects the indirect combustion chamber 402 to the clearance volume 413 at the top of the cylinder 400, to be used to direct the incoming turbocharging air 17 (perhaps at a small angle) towards the piston crown 414. The inclusion of inlet air straightening vanes 416 in the inlet passage 418 behind the inlet valve 408 also helps to direct the incoming air. In this way a "bubble" of clean turbocharging air is positioned on the crown of the piston 414 during an early part of the compression stroke and is maintained with minimum mixing with the combustion gases while the upward movement of the piston pushes the exhaust gas out through the exhaust valves 410. The upward acceleration of the piston at this stage will probably be of assistance in preferentially retaining the denser cooler turbocharging air in the region of the piston crown. Hence, wastage of the turbocharging air in the "purging" process is minimised. The operation cycle of the cylinder configuration shown in Figures 4 and 5 will now be described in more detail with reference to Figures 6 to 9 which illustrate successive stages in the cycle. Figure 2 should also be consulted. It should be noted that for descriptive purposes, the compression stroke is divided into a first (or early) section and a second (or last) section, the first section being subdivided by reference to an initial portion thereof. Figure 6(a) shows the piston 414 within cylinder 400 at a position near Bottom Dead Centre (BDC) near the end of the expansion stroke. The position on the timing diagram of Figure 6(b) is indicated by the large arrow near the bottom. The exhaust valves 410 have just opened, and the inlet valve 408 is just about to open, before BDC is reached. A small amount of combustion gas 420 is already being exhausted to the turbine. Figures -7(a) and 7(b) show the piston just before BDC, with both the inlet valve 408 and the exhaust valves 410 open. This position corresponds approximately to point B on Figure 2. Clean turbocharging air 422 now enters the cylinder and is 18 directed down the cylinder wall 424 (perhaps at a small angle to give some swirl around the cylinder) by the passage 412 to form a "bubble" of clean air on the piston crown. At this point the piston is almost stationary and the incoming turbocharging air 422 displaces some of the combustion gases 420 out of the cylinder through the exhaust valves 410, thus initiating active scavenging or purging of the cylinder. Both the inlet valve 408 and the exhaust valves 410 remain open while the piston moves upwards from BDC during the above-mentioned initial portion of the first or early section of the first or compression stroke of the cycle. This initial portion of the first section of the upward stroke ends when the inlet valve 408 closes somewhat before half-stroke. Figures 8(a) and 8(b) show the piston at a position just before half-stroke, but after shutting of the inlet valve. Active purging by flow-through of the turbocharging air ceases when the inlet valve closes, the upward motion of the piston having helped the "bubble" of relatively clean turbocharging air on top of the piston to push the combustion gases out through the exhaust valves 410. It is preferred that the exhaust valves 410 stay open for a little while longer than the inlet valve 408 to ensure that the cylinder is further scavenged clear of combustion gases. At this stage the combustion gases remaining in the cylinder are concentrated near the exhaust valves and the further upward motion of the piston before the exhaust valves close pushes the combustion gases out of the cylinder. It is preferred that the exhaust valves 410 finally close at a little after half stroke, and Figures 9(a) and 9(b) show the situation somewhat after half-stroke, just after the exhaust valves 410 have closed. Closure of the exhaust valves 410 marks the end of the first or early section of the upward stroke and the beginning of the second or last section, during which compression of the turbocharging air above turbocharging pressure occurs. This position can be identified with point A in Figure 2. As shown in Figure 9(a), during the second section of the compression stroke, the air charge 426 is pushed back into the indirect combustion chamber 402, fuel being injected into the chamber 402 through fuel injector 406 at a point in the second section of the compression stroke somewhat before Top Dead Centre (TDC) . Combustion occurs as the piston passes through TDC, which may be identified approximately with point G in Figure 2. The whole of the second or downward stroke of the cycle is used for expansion, from TDC back .down to BDC, when the cycle repeats. To summarise, therefore, scavenging of the spent combustion gases, including purging with turbocharging air, plus of course induction by turbocharging, are all carried out during the first section of the piston's upward or compressive stroke between points B and A on Figure 2. Note however that both these processes also overlap the end of the expansion stroke slightly in the present example. It will be clear from Figures 6 to 9 why the compression ratio of the diesel engine is much less than the expansion ratio - it is of course because the scavenge and induction process occurs during the compressive stroke of the cycle, before actual compression begins. Although at present it seems preferable to divide the first or early section of the compression stroke into an initial portion, during which both induction and purging by turbocharging air occur, and a final portion, during which further scavenging occurs whilst turbo- charging pressure is maintained in the cylinder by the upward motion of the piston even though the inlet valve has been shut, it may in the light of experimental experience or further theoretical consideration be found more desirable to adjust the valve timing so that the inlet valve closes at the same time as - or even later than - the exhaust valve. It is believed that the cylinder head configuration described with reference to Figures 4 to 9 is suitable for use when the cylinder's expansion ratio is less than about 8. To accommodate greater expansion ratios, a still larger inlet valve area is required, and this object may be achieved by the arrangement shown in Figures 10(a) and 10(b), which shows a view of an indirect combustion chamber taken on a section parallel with the longitudinal axis of the cylinder. Figure 10(a) shows inlet valves 440,442, open and Figure 10(b) shows them shut. The indirect combustion chamber 450 houses a so-called "hot mass" 454 (known in itself) whose, purpose is to assist the combustion process and extend the operational envelope of the engine by retaining heat from the previous cycle. In this way combustion can still proceed in the indirect combustion chamber 450 even if the air inlet temperature is too low to support combustion otherwise. The "hot mass" could be, e.g., a metal grid with a catalytic coating for aiding combustion. The combustion chamber 450 is basically spherical in shape, but has two diametrically opposed inlet ducts 456,458 through which the turbocharging air ' 460 can pass when the inlet valves 440,442, respectively, are open. The inlet valves 440,442, are of the same size and shape and open the inlet ducts 456,458 by moving towards each other along a common axis of movement 462, the arrangement being such that when they are fully open they sandwich the hot mass 454 between them so that it is shielded from the chilling effect of the incoming turbocharging air 460., which then flows into the cylinder (not shown) through a passage 464 similar to passage 412 in Figure 4. A fuel injector, indicated by an arrow 464, sprays fuel into the indirect combustion chamber 450 after the inlet valves have closed, as in Figure 10(b), and combustion occurs as for the previous embodiment. It will be understood that the double opposed inlet valves 440,442 give higher mass flow rates than is possible with only one inlet valve, and hence enable the expansion ratio of the cylinder to be raised to about 12. Referring now to Figures 11 and 12, there is shown a cylinder 500 with a cylinder head 501 similar to that shown in Figures 4 and 5, but incorporating the twin opposed inlet valves 440,442 and hot mass 454 of Figure 10. Where the components are similar to those already described in relation to the Figures just mentioned, they have been given the same reference numerals and neither they nor their function will be described again. Items of note are that the hot mass 454 has been attached conveniently to the end of the heater 404 and that in order to provide the engine with a variable compression ratio, as mentioned in connection with Figure 3, the indirect combustion chamber 502 has been provided with a contra piston 504 which can be moved in and out from the chamber 502 within the duct 506 in the directions of the arrows. The contra piston, of course, is effective to alter the compression ratio by varying the volume of the chamber 502. Whereas Figures 4 to 12 have been concerned with means for performing the proposed 2-stroke cycle comprising cylinder configurations in which the cylinder head incorporates an indirect combustion chamber, Figures 13 to 16 show how the cycle could be achieved using a different configuration of cylinder 600, namely, one like the so-called "ϋniflow" arrangement, in which the turbocharging air enters through fixed inlet ports 602 at the bottom of the cylinder 600 and the spent combustion gases leave through conventional poppet valves 604 in the cylinder head 606. A fuel injector 22 607 injects fuel directly into the top of the cylinder. As will be readily seen from the Figures, the exhaust valve timing is arranged such that the opening and closing of the exhaust valves 604 bears approximately the same relationship to the uncovering and covering of the inlet ports 602 as the opening and closing of the exhaust valves 410 bears to the opening and closing of the inlet valves 408 in Figures 6 to 9. It should be noted that, particularly if the inlet ports are adapted to impart a swirl motion 606 [Figure 14(a)] around the cylinder 600 to the incoming turbocharging air, it will be possible to obtain the desirable "bubble" 608 of clean turbocharging air above the crown of the piston 610 as the piston undergoes its upward compression stroke, thus displacing the spent combustion gases through the exhaust valves 604 in the same way as was accomplished in the earlier-described embodiment.

Claims: 23 Claims:- 1. An operating cycle for a turbocompounded 2-stroke piston engine, said 2-stroke piston engine being adapted to be linked to a turbine/turbocompressor set so that combustion exhaust gases from the piston engine at least partly drive the turbine, which drives the turbocompressor which in turn turbocharges the piston engine; said operating cycle comprising a compression stroke and an expansion stroke, the expansion stroke expanding the combustion gases to a pressure lower than the turbocharging pressure, scavenging of the combustion gases from the piston engine being facilitated by purging the piston engine with turbocharging air during an early part of each compression stroke, whereby the piston engine has a compression ratio which is substantially less than its expansion ratio. 2. An operating cycle according to claim 1, in which the compression ratio of the piston engine is approximately half its expansion ratio. 3. An operating cycle according to claim 2, in which the compression ratio of the piston engine is half its expansion ratio, plus 0.1. 4. An operating cycle according to any one of claims 1 to 3, in which the expansion ratio of the piston engine is in the range 3 to 12 inclusive. 5. An operating cycle according to claim 4 for use at sea level and normal land altitudes, the expansion ratio being in the range 3 to 8 inclusive. 6. An operating cycle according to claim 4 for use at high altitudes, the expansion ratio being in the range 6 to 12 inclusive. 7 . An operating cycle according to any one of claims 1 to 6 in which the piston engine is turbocharged with turbocharging air during an early section of the compression part of the cycle and the turbocharging air is compressed during a last section of the compression part of the cycle, scavenging of combustion gases from the piston engine being aided by purging with turbocharging air during at least an initial portion of said early section of said compression part of the cycle.

Inventors: REES JOHN ANTHONY JENES, REES, JOHN, ANTHONY, JENES
Applicants: REES JOHN ANTHONY JENES, REES, JOHN, ANTHONY, JENES
Application year: 1987
Main classification: F02B41
IPC codes: F02B3, F02B19, F02B23, F02B25, F02B37, F02B41, F02C5, F02C6