RAKH CYCLE - thermodynamic cycle

Abstract

A thermodynamic cycle consisting of six events repeated continuously. Event 1 is adiabatic compression of a carrier gas to raise its temperature. Event 2 is liquid Injection into the hot carrier gas near the end of event 1. Event 3 is temperature equalization between the carrier gas and injected liquid with the liquid's full or partial vaporization. Event 4 is adiabatic expansion of the mixture. Event 5 exhausts the mixture. Exhaust should be captured to save and separate the mixture into its components to increase efficiency, however, this cycle may be either an open or closed cycle. Event 6 is the induction a new charge of carrier gas, which brings the cycle back to the initial conditions of event one. This cyclical sequence of six events numbered from any starting point will be referred to as the RAKH CYCLE. Engines using it are RAKH engines. Refrigeration machines using it are RAKH refrigerators.

Description

BACKGROUND OF INVENTION

[0001] In researching the present invention, I discovered many patents that took advantage of waste heat to increase mechanical work and engine efficiency. Most of these patents selected water as the injected liquid. None of the other patents, however, made use of superheated injected liquids. Typically, ambient water was converted to steam using waste heat of combustion gasses. Each also used internal combustion from an Otto or Diesel cycle to generate the heat. The present invention does not use internal combustion for its heat source. A ‘carrier gas’ is heated outside the engine, via exhaust recovery heat, solar, or some other method. A liquid is also pre-heated externally or by purchasing (or renting) an insulated, pressurized container of the hot liquid.

References Cited

U.S. Patent Documents

[0002]

770468	Sep., 1904	Lake	60/674
917317	Apr., 1909	Lake	60/674
924100	Jun., 1909	Nichols	123/191
1032236	Jul., 1912	Pattern	60/650
1739255	Dec., 1929	Niven	123/193
1926463	Sep., 1933	Stoddard	60/650
2062013	Nov., 1936	Opolo	123/193
3006146	Oct., 1961	Jackson	60/649
3867816	Feb., 1975	Barrett	60/682
3,964,263	Jun. 22, 1976	Tibbs	60/712
4,270,351	Jun. 2, 1981	Kuhns	60/517
4,322,950	Apr. 6, 1982	Jepsen	60/712
4,326,388	Apr. 27, 1982	McFee	62/324.6
4,402,193	Sep. 6, 1983	McFee	62/304
4,553,397	Nov. 19, 1985	Wilensky	60/649
4,691,523	Sep. 8, 1987	Rosado	60/649
5,035,115	Jul. 30, 1991	Ptasinski	60/712
5,983,640	Nov. 16, 1999	Czaja	60/674

DETAILED DESCRIPTION

[0003] The thermodynamic cycle, which is described herein will be called the RAKH CYCLE in respect for all the support I got from my wife, Kay. The said RAKH CYCLE involves a gas or mixture of gasses that are herein referred to as the ‘carrier gas’ and a superheated liquid which vaporizes but does not burn. The purpose of the carrier gas is to bring thermal energy into a volume whereby compression concentrates the thermal energy at a higher temperature. A liquid is then injected. In an engine cycle, the liquid must be superheated above its saturation temperature for the pressure to which the carrier gas will attain at its state of maximum compression. The carrier gas must be much hotter than the injected liquid in order to force heat to be transferred into the injected liquid rapidly. Heat that is transferred from the carrier gas will cool the carrier gas resulting in a lower temperature and pressure. Transfer of the heat from the carrier gas into the liquid, on the other hand, will greatly increase the volume of the injected liquid, through converting it into a vapor. The temperature of the liquid will increase while the temperature of the carrier gas will decrease. The decrease of temperature is offset to a higher value by further compression of the carrier gas due to the vapor produced, which displaces the carrier gas into a smaller volume to accommodate the vapor. All experimental results, which I have derived by calculation, have always resulted in a lower temperature from the end of event one to the end of mixture temperature equalization for event three. This may not be true for real liquids that are injected at pressures above their critical point into a carrier gas that is compressed to a point that is above the critical pressure of the liquid. Some real gasses and liquids exhibit an overall increase in pressure upon vaporization of the liquid in the mixture. The compression phase end temperature of the carrier gas before liquid injection decreases after temperature equalization of the mixture. The present invention covers substances injected above their critical temperature and pressure. These superheated substances are not usually still considered to be liquids. The best choice of carrier gas would not condense at the end pressure. The purpose of the carrier gas is to carry heat into the cycle, which is transferred to a liquid injected at a later point in the cycle after the carrier gas is compressed. Calculations are very difficult because of changing gamma values for the liquid and carrier gas. The preferred implementation uses Argon as the carrier gas and water as the injected liquid. The gamma value for Argon is virtually constant at varying temperatures. The gamma value for H2O at various saturation temperatures is shown in FIG. 1.

[0004] The first event of the RAKH CYCLE is compression of a carrier gas to a maximum compression point with heat added or through strict adiabatic compression. The purpose of this compression is to concentrate the thermal heat via an increase in temperature to force rapid transfer of energy to the liquid injected in event two.

[0005] The second event in this thermodynamic cycle is the injection of liquid into a very nearly constant volume of the gas at the end of the first event. If the cycle is used in an engine, the liquid will be heated to some temperature such that part of the liquid flashes into a gas due to the excess thermal energy of the liquid beyond that of the liquid at its saturation temperature for the pressure in the cylinder (or turbine) arrived at by the mixture.

[0006] Event three in the cycle is equalization of temperature prior to the rapid expansion event, which follows. This third event then includes the transfer of thermal energy from the carrier gas to the injected liquid, which had not yet completely flashed to a gas. If there is a sufficient temperature difference to allow heat to transfer from the carrier gas to the liquid at its saturation temperature and pressure, further vaporization will occur. Complete vaporization is not required for this event. The mixture's pressure may go down during this event. Pressure and or the temperature may be above the critical point for the liquid at the point of injection or after the temperature equalization of event three. In an engine, pressure must increase from that at the end of event 1.

[0007] The fourth event is adiabatic expansion of the mixture. This expansion will likely be back down to the original volume found at the beginning of event one, but may be somewhat more or less. This is where a turbine engine application may have the advantage over a piston engine since the final volume of a piston engine is geometrically constrained to equal event one starting volume. It is very hard to calculate mixture pressure and temperature during expansion so values at each point of expansion were calculated as if the liquid were injected at that point during compression.

[0008] The fifth event is the exhausting of the mixture. The exhaust mixture should be captured into a condenser designed to handle separation of the mixture into its separate components to increase efficiency. This invention, however, does not require a condenser, but does assume a continuous supply of carrier gas and liquid from some source at a constant temperature and pressure.

[0009] Event six is the induction of the carrier gas, which brings the cycle back to the initial conditions of event one whenever the cycle is running in a steady state. This sequence of six events will be repeated as a continuous thermodynamic cycle, which will be referred to as the RAKH CYCLE regardless of the starting point picked for event 1.

[0010] Engines that use this cycle are RAKH engines. Refrigeration machines that use this cycle with appropriate working substances selected for refrigeration are referred to as RAKH refrigerators.

[0011] The selection of the carrier gas and liquid are major impact variables in the cycle efficiencies. The ability of the combination to produce power is a very narrow margin between operable and non-operability of the cycle. The variability of gamma for the real gasses is what allows the cycle to work below the critical point. The gamma value is the ratio of the specific heat at constant pressure to the specific heat at constant volume. For a small adiabatic change of volume, the change of pressure is dependent upon gamma in the relationship: P2=P1 times (V1/V2) raised to the gamma power where P1 is the starting pressure, V1 is the starting Volume, and V2 is the final volume. If gamma is 2 and the compression ratio is 10 then the adiabatic final pressure will be P1 times 100 (10 squared) and not just P1 times 10 as might be expected. The reason for the unexpected increase of pressure is that temperature goes up quickly and raises the pressure even more than would otherwise be expected.

FIGURES AND ILLUSTRATIONS

[0012] FIG. 1 shows the tremendous change in gamma with respect to the starting temperatures for water injected at various superheated temperatures. Using some wider range standardized thermodynamic data tables or empirical data from actual experimentation beyond the critical point of water may reveal an even more efficient engine, operating in an injection temperature range above the data range used for calculations herein. The greater the pressure increase caused by events 2 and 3 in the RAKH Cycle, the more power the engine can develop.

[0013] FIG. 2 shows that calculated engine efficiency increases directly proportional to the injection temperature. Minimizing the necessity for adding latent heat tends to increase RAKH Cycle engine efficiency by preserving the temperature of the carrier gas. Considered separately, the absolute pressure of the carrier gas is directly proportional to its absolute temperature at a constant volume. FIG. 2 uses the preferred carrier gas of Argon and water injected at various superheated temperatures. Some further experimentation or theoretical extrapolations of temperatures beyond the critical point may yield a still more efficient yet practical engine. The increase of pressure caused by RAKH Cycle events 2 and 3 can be increased by minimizing the necessity for adding latent heat. Supplying the latent heat, robs the carrier gas of its heat in the form of a lowered temperature. Thus its pressure will decrease too, which reduces the power.

[0014] FIG. 3 shows power and efficiency versus the quantity of water injected at two different initial carrier gas temperatures, the higher the better. Too much water chokes the power and efficiency.

[0015] FIG. 4 graphs various compression ratios per a highly iterative computer program simulation of a piston engine compression and power strokes.

[0016] Listings 1 through 6 are computer calculated simulation printouts for various compression ratios, carrier gas initial temperatures, and pressures, with optimized water injection masses. Gamma values were changed in the program at frequent intervals for the injected water. The program calculated temperature and pressure of the expanding mix for each two degrees of crank rotation. Listings show efficiency increases when compression ratios or temperatures are increased.

[0017] Figures and Illustrations

[0018] Listing 1 is a computer printout for 8:1 compression at 1200 deg. F. starting gas temperature.

[0019] Argon @ STP=39.948 grams for 22.4 liters

[0020] Cp=0.133; Cv=0.075165; gamma=1.769441

[0021] T2=7760.784 deg. F. & P2=2813.341 psia; Head Vol.=62.5 cc; CR=8:1; free Ambient=300 deg. F.

[0022] Argon Pres/Temp compensated mass in grams=1.37449

[0023] Thermal energy per power cycle to heat Argon=0.2049907 BTUs

[0024] Assumed free feed Water heat=268 BTUs per pound

[0025] Thermal energy per power cycle to heat Water=7.598673E-02 BTUs

[0026] Mechanical work done to compress the Argon is −928.0307 ft-lbs

[0027] Event 2

[0028] At TDC, inject 0.06 grams of superheated Water at 704 deg. F. % Mole mass Argon=95.81733% %Mole mass H2O=4.18267%

[0029] Since the injected Water is superheated, some flashes to vapor;

[0030] Volume .06 grams of Saturated vapor at 2784.7 psia=0.390925 cc So, Argon is further compressed and now occupies only 62.10907 cc

[0031] The cylinder pressure however, decreases to 2784.7 psia as a result of all the Water converting to saturated vapor and the carrier gas temperature changes to 7638.407 Equalizing temperatures, the vapor's temperature goes up to meet Argon's decreasing temperature at 5692.219 deg. F.

[0032] 8:1 Compression of Argon starting @ 1200 deg. F. & 71 psia

[0033] Calculating partial volumes of 0.06 grams Water vapor & 1.37449 grams Argon yields 4.551353 & 57.94865 cc respectively after equalizing temperatures.

[0034] Sums of the partial volumes must equal the cylinder volume of 62.5 at TDC.

Angle	Temp. F	PSIA	Cyl Vol	Steam	Argon
90	5692.219	2983.976	62.5	4.5513 SUP	57.94865
80	5415.021	2657.699	66.60092	4.9205 SUP	61.68034
70	4747.316	1959.702	78.80437	5.9693 SUP	72.83501
60	3973.675	1307.761	98.53674	7.6205 SUP	90.91614
50	3265.964	851.2669	124.8817	9.8463 SUP	115.0354
40	2691.061	564.1493	156.6411	12.607 SUP	144.0338
30	2241.762	387.6474	192.4153	15.710 SUP	176.7049
20	1897.452	278.4525	230.6973	19.435 SUP	211.2621
10	1624.841	208.0506	269.9732	22.626 SUP	247.347
0	1416.888	163.8102	308.8161	28.522 SUP	280.2934
−10	1254.789	132.4055	345.9635	32.056 SUP	313.9067
−20	1131.672	110.5387	380.3672	33.588 SUP	346.7791
−30	1035.548	93.85143	411.2137	31.029 SUP	380.1843
−40	963.3055	82.05675	437.9155	25.810 SUP	412.1045
−50	908.7077	74.63467	460.0805	22.649 SUP	437.4312
−60	868.5814	69.51414	477.4703	20.515 SUP	456.955
−70	841.2895	66.18478	489.955	19.153 SUP	470.801
−80	827.2404	64.29819	497.4729	18.418 SUP	479.0547
−90	820.8011	63.6814	499.9999	18.153 SUP	481.8467
Exhaust pressure of the binary mixture is 63.6814 psia at 820.8011 degrees F.
Work done is 947.6757 ft-lbs; Estimated W-9 Horsepower @ 3600 RPM = 9.644 hp
Estimated heat for Argon = 55.3475 BTU/sec and for liquid = 20.51642 BTU/sec
Theoretical Efficiency = 8.983552%

[0035] Figures and Illustrations

[0036] Listing 2 is a computer printout for 8:1 compression at 1400 deg. F. starting gas temperature.

[0037] Argon @ STP=39.948 grams for 22.4 liters

[0038] Cp=133; Cv=0.075165; gamma=1.769441

[0039] T2=8751.396 deg. F. & P2=2813.341 psia; Head Vol.=62.5 cc; CR=8:1; free Ambient=300 deg. F.

[0040] Argon Pres/Temp compensated mass in grams=1.22667

[0041] Thermal energy per power cycle to heat Argon 0.2235992 BTUs

[0042] Free feed Water heat=268 BTUs per pound

[0043] Thermal energy per power cycle to heat Water=7.598673E-02 BTUs

[0044] Mechanical work done to compress the Argon is −928.0307 ft-lbs

[0045] Event 2

[0046] At TDC, inject 0.06 grams of superheated Water at 704 deg. F. % Mole mass Argon 95.3368% % Mole mass H2O=4.663202%

[0047] Since the injected Water is superheated, some flashes to vapor;

[0048] Volume 0.06 grams of Saturated vapor at 2784.7 psia=0.3909251cc So, Argon is further compressed and now occupies only 62.10907 cc

[0049] The cylinder pressure however, decreases to 2784.7 psia as a result of all the Water converting to saturated vapor and the carrier gas temperature changes to 8614.273 Equalizing temperatures, the vapor's temperature goes up to meet Argon's decreasing temperature at 6153.344 deg. F.

[0050] 8:1 Compression of Argon starting @ 1400 deg. F. & 71 psia

[0051] Calculating partial volumes of 0.06 grams Water vapor & 1.22667 grams Argon yields 4.858467 & 57.64153 cc respectively after equalizing temperatures.

[0052] Sums of the partial volumes must equal the cylinder volume of 62.5 at TDC.

Crank
Angle	Temp. F	PSIA	Cyl Vol	Steam	Argon
90	6153.344	2999.854	62.5	4.8584 SUP	57.64153
80	5862.012	2672.399	66.60092	5.2606 SUP	61.34026
70	5153.316	1971.232	78.80437	6.3964 SUP	72.40793
60	4326.985	1315.87	98.53674	8.1837 SUP	90.35295
50	3575.412	856.8443	124.8817	10.600 SUP	114.2809
40	2964.404	568.0646	156.6411	13.612 SUP	143.0291
30	2475.762	390.3107	192.4153	16.938 SUP	175.4763
20	2105.5	280.4383	230.6973	20.979 SUP	209.7177
10	1816.841	209.6149	269.9732	24.602 SUP	245.3707
0	1590.476	165.1332	308.8161	30.892 SUP	277.9238
−10	1414.789	133.8045	345.9635	34.761 SUP	311.2022
−20	1279.843	111.3988	380.3672	36.596 SUP	343.7709
−30	1175.548	94.80654	411.2137	34.345 SUP	376.8687
−40	1095.426	82.59328	437.9155	28.434 SUP	409.4808
−50	1035.117	74.75674	460.0805	24.783 SUP	435.2975
−60	992.4648	69.61333	477.4703	22.471 SUP	454.9989
−70	962.9454	66.27042	489.955	20.988 SUP	468.9663
−80	945.4143	64.37533	497.4729	20.152 SUP	477.3203
−90	938.8011	63.75652	499.9999	19.869 SUP	480.1304
Exhaust pressure of the binary mixture is 63.75652 psia at 938.801 degrees F.
Work done is 953.8967 ft-lbs; Estimated W-9 Horsepower @ 3600 RPM = 12.697 hp
Estimated heat for Argon = 60.37178 BTU/sec and for liquid = 20.51642 BTU/sec
Theoretical Efficiency = 11.09368%

[0053] Figures and Illustrations

[0054] Listing 3 is a computer printout for 10:1 compression at 1200 deg. F. starting gas temperature.

[0055] Argon @ STP=39.948 grams for 22.4 liters

[0056] Cp=0.133 Cv=0.075165 gamma=1.769441

[0057] T2=9300.61 deg. F. & P2=2764.002 psia; Head Vol.=50 cc; CR =10:1;

[0058] free Ambient=300 deg. F.

[0059] Argon Pres/Temp compensated mass in grams=0.9098739

[0060] Thermal energy per power cycle to heat Argon=0.1356981 BTUs

[0061] Free feed Water heat=268 BTUs per pound

[0062] Thermal energy per power cycle to heat Water=6.332228E-02 BTUs

[0063] Mechanical work done to compress the Argon is −758.6626 ft-lbs

[0064] Event 2

[0065] At ADC, inject 0.05 grams of superheated Water at 704 deg. F. % Mole mass Argon=94.79099% % Mole mass H2O=5.209018%

[0066] Since the injected Water is superheated, some flashes to vapor;

[0067] Volume 0.05 grams of Saturated vapor at 2732.787 psia=0.3402922cc

[0068] So, Argon is further compressed and now occupies only 49.65971 cc

[0069] The cylinder pressure however, decreases to 2732.787 psia as a result of all the Water converting to saturated vapor and the carrier gas temperature changes to 9141.189 Equalizing temperatures, the vapor's temperature goes up to meet Argon's decreasing temperature at 6281.403 deg. F.

[0070] 10:1 Compression of Argon starting @ 1200 deg. F. & 47 psia Calculating partial volumes of 0.05 grams Water vapor & 0.9098739 grams Argon yields 4.185383 & 45.81462 cc respectively after equalizing temperatures.

[0071] Sums of the partial volumes must equal the cylinder volume of 50 at TDC.

Angle	Temp. F	PSIA	Cyl Vol	Steam	Argon
90	6281.403	2961.447	50	4.1853 SUP	45.8146
80	5912.367	2556.354	54.21809	4.6300 SUP	49.5880
70	5050.044	1754.167	66.77021	5.8883 SUP	60.8818
60	4106.926	1084.716	87.06635	7.8927 SUP	79.1735
50	3294.834	663.436	114.1641	10.626 SUP	103.5371
40	2663.506	419.4027	146.8309	13.996 SUP	132.8349
30	2186.437	278.9729	183.6271	18.161 SUP	165.4661
20	1825.887	195.0003	223.0029	22.377 SUP	200.6253
10	1545.998	144.5772	263.401	29.013 SUP	234.3875
0	1334.585	110.1319	303.3537	31.682 SUP	271.6711
−10	1173.009	85.30632	341.5625	25.712 SUP	315.8498
−20	1050.427	69.7062	376.9491	19.498 SUP	357.4505
−30	956.1718	59.6932	408.6769	15.727 SUP	392.9495
−40	884.814	52.40205	436.1416	13.106 SUP	423.0352
−50	830.8615	47.46509	458.9399	11.402 SUP	447.5375
−60	794.1226	44.09988	476.8266	10.295 SUP	466.5308
−70	768.5775	41.89244	489.6679	9.5812 SUP	480.0866
−80	753.5972	40.63806	497.4006	9.1804 SUP	488.2202
−90	749.0366	40.22953	499.9999	9.0537 SUP	490.9461
Exhaust pressure of the binary mixture is 40.2295 psia at 749.0366 degrees F.
Work done is 778.1189 ft-lbs, Estimated W-9 Horsepower @ 3600 RPM = 9.551 hp
Estimated heat for Argon = 36.6385 BTU/sec and for liquid = 17.0970 BTU/sec
Theoretical Efficiency = 12.5612%

[0072] Figures and Illustrations

[0073] Listing 4 is a computer printout for 10:1 compression at 1400 deg. F. starting gas temperature.

[0074] Argon @ STP=39.948 grams for 22.4 liters

[0075] Cp=0.133; Cv=0.075165; gamma=1.769441

[0076] T2=10476.78 deg. F. & P2=2764.002 psia; Head Vol. 50 cc; CR=10:1;

[0077] free Ambient=300 deg. F.

[0078] Argon Pres/Temp compensated mass in grams=.8120207

[0079] Thermal energy per power cycle to heat Argon=0.1480163 BTUs

[0080] Free feed Water heat=268 BTUs per pound

[0081] Thermal energy per power cycle to heat Water=6.332228E-02 BTUs

[0082] Mechanical work done to compress the Argon is −758.6626 ft-lbs

[0083] Event 2

[0084] At ADC, inject 0.05 grams of superheated Water at 704 deg. F. % Mole mass Argon=94.19968% % Mole mass H2O 5.800325%

[0085] Since the injected Water is superheated, some flashes to vapor;

[0086] Volume 0.05 grams of Saturated vapor at 2732.787 psia=0.3402922 cc So, Argon is further compressed and now occupies only 49.65971 cc

[0087] The cylinder pressure however, decreases to 2732.787 psia as a result of all the Water converting to saturated vapor and the carrier gas temperature changes to 10298.16 Equalizing temperatures, the vapor's temperature goes up to meet Argon's decreasing temperature at 6727.823 deg. F.

[0088] 10:1 Compression of Argon starting @ 1400 deg. F. & 47 psia

[0089] Calculating partial volumes of 0.05 grams Water vapor & 0.8120207 grams Argon yields 4.432171 & 45.56783 cc respectively after equalizing temperatures.

[0090] Sums of the partial volumes must equal the cylinder volume of 50 at TDC.

Angle	Temp. F	PSIA	Cyl Vol	Steam	Argon
90	6727.823	2977.473	50	4.4321 SUP	45.5678
80	6338.564	2570.751	54.21809	4.9082 SUP	49.3098
70	5432.52	1764.889	66.77021	6.2589 SUP	60.5112
60	4438.989	1092.14	87.06635	8.4068 SUP	78.6595
50	3582.834	668.1401	114.1641	11.363 SUP	102.8006
40	2915.923	422.6461	146.8309	15.036 SUP	131.794
30	2400.371	281.1099	183.6271	19.452 SUP	164.1748
20	2020.208	196.4961	223.0029	23.954 SUP	199.0484
10	1719.998	145.9168	263.401	31.284 SUP	232.1168
0	1492.543	111.1008	303.3537	34.328 SUP	269.025
−10	1317.009	85.7609	341.5625	28.119 SUP	313.4429
−20	1182.627	69.81921	376.9491	21.228 SUP	355.7203
−30	1080.743	59.76393	408.6769	17.135 SUP	391.5417
−40	1002.673	52.79094	436.1416	14.416 SUP	421.7255
−50	944.4111	47.52547	458.9399	12.440 SUP	446.4995
−60	902.3192	44.14756	476.8266	11.216 SUP	465.6096
−70	873.3138	41.93295	489.6679	10.429 SUP	479.238
−80	857.5972	40.67531	497.4006	9.9988 SUP	487.4018
−90	851.0366	40.26515	499.9999	9.8487 SUP	490.1512
Exhaust pressure of the binary mixture is 40.2651 psia at 851.0366 degrees F.
Work done is 783.384 ft-lbs; Estimated W-9 Horsepower @ 3600 RPM 12.1361 hp
Estimated heat for Argon = 39.96441 BTU/sec and for liquid = 17.0970 BTU/sec
Theoretical Efficiency = 15.03015%

[0091] Figures and Illustrations

[0092] Listing 5 is a computer printout for 12:1 compression at 1200 deg. F. starting gas temperature.

[0093] Argon @ STP=39.948 grams for 22.4 liters

[0094] Cp=133 Cv=0.075165 gamma=1.769441

[0095] T2=10770.53 deg. F. & P2=2760.743 psia; Head Vol.=41.6667 cc; CR=12:1;

[0096] free Ambient=300 deg. F.

[0097] Argon Pres/Temp compensated mass in grams=0.6582066

[0098] Thermal energy per power cycle to heat Argon 9.816456E-02 BTUs

[0099] Free feed Water heat=268 BTUs per pound

[0100] Thermal energy per power cycle to heat Water=4.432559E-02 BTUs

[0101] Mechanical work done to compress the Argon is −648.5344 ft-lbs

[0102] Event 2

[0103] At TDC, inject 0.035 grams of superheated Water at 704 deg. F. % Mole mass Argon=94.951% % Mole mass H2O=5.048999%

[0104] Since the injected Water is superheated, some flashes to vapor;

[0105] Volume 0.035 grams of Saturated vapor at 2734.399 psia=0.2378876 cc So, Argon is further compressed and now occupies only 41.42878 cc

[0106] The cylinder pressure however, decreases to 2734.399 psia as a result of all the Water converting to saturated vapor and the carrier gas temperature changes to 10615.93 Equalizing temperatures, the vapor's temperature goes up to meet Argon's decreasing temperature at 7199.492 deg. F.

[0107] 12:1 Compression of Argon starting 8 1200 deg. F & 34 psia

[0108] Calculating partial volumes of 0.035 grams Water vapor & 0.6582066 grams Argon yields 3.331799 & 38.33487 cc respectively after equalizing temperatures.

[0109] Sums of the partial volumes must equal the cylinder volume of 41.6667 at TDC.

Angle	Temp. F	PSIA	Cyl Vol	Steam	Argon
90	7199.492	2954.399	41.66667	3.3317 SUP	38.33487
80	6693.274	2474.644	45.96288	3.7609 SUP	42.20195
70	5581.69	1590.765	58.74744	4.9866 SUP	53.76077
60	4434.087	923.742	79.41944	6.9565 SUP	72.46288
50	3495.073	539.0018	107.019	9.6969 SUP	97.32202
40	2790.533	329.7793	140.2907	13.082 SUP	127.2083
30	2267.495	214.0209	177.7684	16.943 SUP	160.8246
20	1881.981	148.6708	217.8733	23.112 SUP	194.7608
10	1588.337	106.9171	259.0196	25.766 SUP	233.2534
0	1365.485	78.10737	299.7121	18.435 SUP	281.2764
−10	1198.119	61.58424	338.6284	13.282 SUP	325.3464
−20	1069.991	50.85831	374.6704	10.164 SUP	364.5055
−30	972.6651	43.53189	406.9858	8.1669 SUP	398.8188
−40	899.26	38.05911	434.9591	6.7535 SUP	428.2055
−50	843.4289	34.49232	458.1796	5.8702 SUP	452.3094
−60	805.2305	32.01327	476.3975	5.2878 SUP	471.1096
−70	778.4795	30.39824	489.4766	4.9135 SUP	484.5631
−80	764.2328	29.48538	497.3525	4.7102 SUP	492.6423
−90	758.4092	29.18753	499.9999	4.6399 SUP	495.36
Exhaust pressure of the binary mixture is 29.1875 psia at 758.4092 degrees F.
Work done is 666.9431 ft-lbs; Estimated W-9 Horsepower @ 3600 RPM = 9.0370 hp
Estimated heat for Argon = 26.50443 BTU/sec
Estimated heat for injected liquid = 11.96791 BTU/sec
Theoretical Efficiency = 16.59994%

[0110] Figures and Illustrations

[0111] Listing 6 is a computer printout for 12:1 compression at 1400 deg. F. starting gas temperature.

[0112] Argon @ STP=39.948 grams for 22.4 liters

[0113] Cp=133 Cv=0.075165 gamma=1.769441

[0114] T2=12123.84 deg. F. & P2=2760.743 psia; Head Vol.=41.6667 cc; CR =12:1;

[0115] free Ambient=300 deg. F.

[0116] Argon Pres/Temp compensated mass in grams=0.5874192

[0117] Thermal energy per power cycle to heat Argon=0.1070757 BTUs

[0118] Free feed Water heat=268 BTUs per pound

[0119] Thermal energy per power cycle to heat Water=4.432559E-02 BTUs

[0120] Mechanical work done to compress the Argon is −648.5344 ft-lbs

[0121] Event 2

[0122] At ADC, inject 0.035 grams of superheated Water at 704 deg. F. % Mole mass Argon=94.37678% % Mole mass H2O=5.62322%

[0123] Since the injected Water is superheated, some flashes to vapor;

[0124] Volume 0.035 grams of Saturated vapor at 2734.399 psia=0.2378876cc So, Argon is further compressed and now occupies only 41.42878 cc

[0125] The cylinder pressure however, decreases to 2734.399 psia as a result of all the Water converting to saturated vapor and the carrier gas temperature changes to 11950.6 Equalizing temperatures, the vapor's temperature goes up to meet Argon's decreasing temperature at 7714.418 deg. F.

[0126] 12:1 Compression of Argon starting @ 1400 deg. F. & 34 psia

[0127] Calculating partial volumes of 0.035 grams Water vapor & 0.5874192 grams Argon yields 3.532375 & 38.13429 cc respectively after equalizing temperatures.

[0128] Sums of the partial volumes must equal the cylinder volume of 41.6667 at TDC.

Angle	Temp. F	PSIA	Cyl Vol	Steam	Argon
90	7714.418	2969.924	41.66667	3.5323 SUP	38.1342
80	7173.274	2488.044	45.96288	3.9886 SUP	41.9742
70	6005.69	1600.18	58.74744	5.3040 SUP	53.4433
60	4794.087	929.7141	79.41944	7.4253 SUP	71.9941
50	3802.525	542.8007	107.019	10.385 SUP	96.6333
40	3053.34	332.2596	140.2907	14.051 SUP	126.2389
30	2489.76	215.678	177.7684	18.227 SUP	159.541
20	2079.981	149.9546	217.8733	24.869 SUP	193.0038
10	1766.371	107.7979	259.0196	27.897 SUP	231.1217
0	1527.485	78.36844	299.7121	20.123 SUP	279.5889
−10	1344.46	61.65889	338.6284	14.465 SUP	324.1626
−20	1205.932	50.90034	374.6704	11.079 SUP	363.5905
−30	1098.773	43.55795	406.9858	8.8979 SUP	398.0878
−40	1019.412	38.42031	434.9591	7.4608 SUP	427.4982
−50	959.3326	34.51474	458.1796	6.4075 SUP	451.7721
−60	915.2305	32.03089	476.3975	5.7622 SUP	470.6352
−70	886.4795	30.41343	489.4766	5.3566 SUP	484.12
−80	868.9189	29.49901	497.3525	5.1273 SUP	492.2252
−90	864.4092	29.20099	499.9999	5.0581 SUP	494.9417
Exhaust pressure of the binary mixture is 29.2010 psia at 864.4092 degrees F.
Work done is 671.0901 ft-lbs, Estimated W-9 Horsepower @ 3600 RPM = 11.073 hp
Estimated heat for Argon = 28.9104 BTU/sec and for liquid = 11.9679 BTU/sec
Theoretical Efficiency = 19.14237%

[0129] Conclusion

[0130] The enclosed figures show that efficiency increases with increasing compression and increasing temperatures as would be expected but power seems to decrease. Increasing the temperature of the injected liquid produces a nearly linear increase in efficiency as shown by FIG. 2. Aditional data on super critical liquid injection temperatures and pressures should yield further increases.

[0131] The present invention makes it possible to develop an externally heated non-polluting engine. The cycle can use a preheated supply of liquid for direct injection. In an automotive application, the liquid can be heated prior to getting onto the road. The carrier gas may be straight air or cheaper, throw-away gasses like Oxygen, Nitrogen, or possibly even Argon for use in an open thermodynamic cycle. The carrier gas may also be more expensive gasses that are contained within a closed thermodynamic cycle. Using oxygen as the carrier gas, it may show a practical, high efficiency application for a boron/oxygen type engine. Using the boron/oxygen as a recyclable heat source creates a pollution free heat source for automotive power applications. The combustion products are Hot Oxygen and Boron oxide which is a glassy solid. Any pollution free or reduced emissions heating source is good for automotive applications because certain pollutants are hard to eliminate in internal combustion engines. Using a high quality molecular sieve to separate pure oxygen from the air may become more practical with moderate technological advances.

[0132] The ability to add a bottoming cycle to the superheated steam and gas mixture leaving a RAKH CYCLE engine as exhaust may allow for further gains of efficiency. This thermodynamic cycle actually creates a physical phase change diode, similar to the electrical diode. The phase change takes place due to concentration of heat manifested as a temperature increase. The phase change in the cycle occurs without a boiler. The compressed volume of the carrier gas is better than a boiler since the heat in a boiler has to pass through a heat exchanger. In this cycle, direct contact with the heat source causes a rapid, nearly explosive, phase change.

[0133] Using Helium as the carrier gas may allow easy molecular separation of the liquid from the carrier gas without condensing the liquid. The benefit of that ability would be a selective application of condenser cooling to the liquid without having to remove heat from the carrier gas. All of the noble gasses, being inert, are easier to heat without worry of corrosion from the gas. They also have an ultra-flat gamma value across a very wide range of temperatures.

[0134] Some combinations of carrier gasses and injected liquids do not exhibit an increase of pressure as the heat of the carrier gas is used to vaporize the injected liquid. The corresponding loss of temperature coincides with a corresponding decrease in the pressure. This pressure drop takes an overall input of work to enable continued operation rather than producing work as an engine must if is to be called an engine. An optimal gas and liquid pairing for an excellent operational engine would necessarily utilize only a small drop in temperature of the carrier gas in order to vaporize the liquid with a resulting large increase in pressure from a small amount of latent heat added. Not much experimentation has been done in the effort of finding substances to present a thermodynamic RAKH CYCLE with optimal conditions for producing power and efficiency. It works, but much must be done to justify its use over other thermodynamic cycles in terms of cost benefit for such a pollution free yet low power engine albeit one with such reasonable efficiency. Oerating temperatures and pressures will provide significant technological challenges as well.

Claims

1. A thermodynamic engine power cycle that uses a carrier gas, which is compressed to increase its temperature so that a superheated liquid may be injected into the hot carrier gas and result in pressure increase to generate power from a portion of the heat input via the gas and the liquid. Over-pressurized, superheated liquid is injected and mixes with a hotter carrier gas at a pressure below the saturation pressure corresponding to the temperature of the liquid, causing full or partial liquid vaporization that results in a net increase in pressure upon equalization of temperatures for the mixture. The increase of pressure is then extracted as work during adiabatic expansion of the mixture. Engine power is very dependent upon selection of the proper working carrier gas and injected liquid at effective temperatures and pressures, which are compatible with an increase of pressure for the mixture. This invention covers the identified thermodynamic engine cycle using any gasses and liquids, which exhibit an increase of pressure with the necessary incidental decrease in carrier gas temperature due to transfer of thermal energy to the injected liquid in the mixture. Combustion of the carrier gas and/or the injected liquid is not a required heat source for an engine that is covered by the present invention .

2. A thermodynamic refrigeration cycle, which uses any said real carrier gas that is compressed to concentrate thermal energy during a compression event that increase the temperature of the carrier gas and achieves rapid cooling upon injection of a liquid substance that takes up part of the heat of the carrier gas in vaporizing some or all of the injected liquid. The temperature of the mixture at an end pressure achieved during adiabatic expansion of the mixture is lower than the initial temperature of the carrier gas.

3. This thermodynamic cycle is covered with arbitrary selection of any cycle event of the said RAKH cycle as the first event with the rest of the events in the same relative cyclical sequence. Combining or adding events in the cycle are covered as long as the essence the cycle relies on transfer of concentrated thermal energy in the form of increased temperature due to compression of a carrier gas and subsequent transfer of a portion of that thermal energy to an injected substance, which increases overall pressure of the mixture after equalization of their temperatures.

4. A thermodynamic cycle is covered by the scope of this invention even if the substance injected is pressurized above the critical pressure of the liquid phase of that substance.

5. A thermodynamic cycle is covered by the scope of this invention even if the substance injected into the compressed volume of the carrier gas is injected at a temperature above the critical temperature for the liquid phase of that substance.

6. A two stroke or four stroke or any other superficial mechanical implementation or even turbines engines are covered in this thermodynamic cycle as well as is any other means of generating the cycle mechanically, including turbocharging or supercharging the carrier gas.

7. Other patent claims may restrict and protect use of certain patented, or yet to be patented substances, which may optimize certain characteristics of the carrier gas or the injected liquids but will still constitute no more than just a specific implementation of this RAKH Cycle when used within the thermodynamic cycle described under the present invention.