Dec- 3, 1945- A D. F. WARNER EI'AL ‘ 2,412,071 CABIN SUPERCHAKGING MEANS HAVING AUTOMATIC PRESSURE AND TEMPERATURE CONTROL MEANS Filed July 22, 1944 / ‘Fi 3.1’. , I 52 Sheets-Sheet 1 I; 26' x85 066" ,9. . ‘Inventor-5:’ Donald F: Warner, Earl L. Auger‘, My 61/ Their- Attorney. 2,412,071 . 3, 1946. . D. F. WARNER ET AL CABIN SUPERCHARGING MEANS HAVING AUTOMATIC PRESSURE AND TEMPERATURE CONTROL MEANS ' Filed July 22, 1944 2 Sheets-Sheet 2 ‘Us & .r....M Hg 4 fsnpzrafur: I94 Q lnventovsi Donald F Warner‘, ‘ by Ea‘r-l- IL). Auger, ,Jqwéwq Their- AttorT-‘leg Patented Dec. 3, 1946 * 2,412,071 UNITED ‘STATES? PATENT oer-"ice ? 2,412,071 CABIN SUPERCHARGING MEANS HAVING AUTOMATIC PRESSURE AND TEMPERA ' TURE CONTROL MEAN S- - Donald Fl Warner and Earl L. Auyer, Swamp scott, Mass., assignors to-General Electric Com pany, a corporation of New York Application July 22, 1944, Serial _No. 546,717 ,~ 13>Claims. (CI. 98-15) . 1 - e The present invention relates to cabin super and has for its- object to provide an improved system for supplying supercharged air to a cabin and regulating its pressure, temperature and rate _ For a consideration of what we believe to be novel and our invention, attention is directed to the following speci?cation and to the claims ap pended thereto. . 10 On one end, it is provided with a bevel gear l6 In the drawings, Fig. 1 is a side view of a cabin supercharger structure embodying our invention, it being shown attached to a cabin wall of an aircraft cabin; Fig. 2 ‘is a diagrammatic view illustrating our system; Fig. 3 is a perspective exploded view of a portion of the structure shown in Fig. l, and Fig. 4 is a detail view of a modi?ca tion. ' 2. type and may utilize air from the slip stream of the aircraft for cooling medium. It is shown diagrammatically as comprising cooling tubes through which the air ?ows to the cabin and over which the slipstream air ?ows. Air?ow from ‘the mixing chamber through conduits II and I2 is' apportioned between them by a flap valve I4 car ried by apshaft I5 pivoted in walls of ‘easing 2. charger systems such as are used on aircraft of ?ow. _ duit l2 to the cabin. It may be of any suitable ' Referring to the drawings, I indicates the cabin of an aircraft which is to be supercharged, ven tilated and heated. As shown in Fig. 1, our im proved mechanism comprises a unitary structure which‘meshes with a bevel gear I‘! on‘ the shaft of a reversing electric motor l8, the two ?eld _ windings of which are indicated at l9 and 20. Motor I8 is carried by a suitable bracket depend ing from and securedv to housing 2 as ‘shown clearly in Figs. 1 and 3. ‘ , . ' Air?ow through conduit 6 ‘is controlled by a rotary valve 2| mounted in a casing 22. Valve 2| rotates in a counterclockwise direction as indi- ‘ cated by the arrow in Fig. 2 and the arrange ment is such that it must rotate through .a pre determined angle before it starts to open. It is ‘mounted on a shaft 23 pivoted in walls of con which is bolted directly to a wall of the cabin duits'B and ‘I. Also, in conduit 6 beyond valve as a unit. It comprises a rectangular casing'2 2| as regards the ?ow of .air through conduit which forms a mixing chamber, is'open at its ‘ 6 is a valve 24 which is manually operated,'it ‘two ends and is provided with end bolting ?anges being normally in open position, as shown in Fig. 3 and 4. Attached to bolting ?ange 3 is an end 2. The arrangement is such that it may be oper wall 5 formed integral with the adjacent ends ‘ ated from within the cabin. To this end, it may of two conduits 6 and 1 which at their other ends 30 be connected by suitable links and levers 25, as are integral with a second end wall 8. Attached indicated particularly in Fig. 1, tov an- operating to end Wall 8 and communicating with conduit rod 26 which terminates at a suitable point with 6 is a "pipe line 9 which leads from a'source ' in the cabin. of hot pressurized or supercharged air. For ex Flow of air through conduit 1 is controlled by ample, it may be a branch pipe line connected two'valves 21 and 28. Valve 21 is mounted on 35 with the discharge side of the compressor of a shaft 23 so that it rotatesi in unison with valve turbosupercharger or of a gas turbine power 2|. The shaft 23 is provided on its outer end plant. Thus there is supplied through pipe 9 with da gear 29 which meshes with _a gear 38 air of a temperature and pressure both higher mounted on the shaft 3| ‘of a reversing electric than that desired for the cabin. Attached to end wall 8 and communicating with conduit 'Iis a 40 motor 32, the ?elds of which are indicated at 33 and 34. Valve 28 is mounted on a shaft 35 piv-‘ ‘ pipe line 10 which terminates in an open end oted in the wall of conduit 1. On its outer end, facing into the aircraft slip stream or communi it is provided with an arm 36 connected by a link _ ' cates with a plenum chamber having an open ing facing into the slip stream. Thus there‘is 45 31 to an arm 38 fixed on shaft l5. Thus, it will be seen that valves l4 and 28 are both con ' supplied through pipe line I0 to conduit 1 rammed nected to motor [8 and are operated by it. atmospheric air, the pressure and temperature ‘The reversing ?elds 33 and 34 of motor 32 are of which may vary widely with the speed and alti connected‘ through limit switches 39 and 48 to tude of the aircraft. ' the stationary contacts 4| and 42 of a vacuum Connected to bolting ?ange 4 are walls which 50 switch 43. The movable contact '44 of vacuum de?ne two conduits H and i2 which at one end switch 43, which is pivoted in the end wall of the communicate with the mixing chamber of casing vacuum‘switch, is connected at its outer end to a 2 and at the other end are connected to the lever '45 carried by a pivot‘ pin 45 ‘mounted in ‘cabin. They serve toj convey air from the mix-' I ing chamber to the cabin. a casing 41. Mounted on a wall of casing 41 on In- conduit I2 is a‘ 55 opposite sides of pivot pin 46 are two corrugated \ - cooler l3 for cooling the air ?owing through con V 7 2,412,071 bellows 48 and 49. The movable end of bellows ; 48 is pivotally connected to lever 45 as is indi cated at 58 (see Fig. 3). Its interioris con nected by a pipe 5| to the mixing chamber formed by easing 2. Thus, bellows 48 is subjected on 4 18 to atmosphere. For use in effecting flow of air from the cabin to atmosphere under certain operating conditions, there is provided an ejector which utilizes as operating ?uid supercharged air ' its interior to the pressure in the mixing chamber ' _ taken preferably from conduit 8 in advance of . valve 2|. To this end, there are provided in con which pressure is used as a measure of the pres " nection with the outer of the walls 11, walls 19 sure in the cabin. Bellows 49 is evacuated and - which de?ne a pressure air chamber 88. is provided on its interior with a spring 52 which ‘ Air chamber 88 is connected by a pipe 8| to conduit 8 acts normally in a direction to distend the bel 10 in advance of valve_2|.v Connected with cham- ‘ lows. Bellows 49 and spring 52 have a charac-V/ ber 88 is a discharge nozzle 82 which'projects teristic such that below a certain altitude the across air chamber 16 and terminates at the movable end of the bellows is not in engagement throat of discharge nozzle 18 to form with the with lever 45, ‘but after reaching a certain alti discharge nozzle an ejector of known construc tude the movable end engages lever 45 and is tion. Flow of air from chamber 88 to discharge adapted to eifect movement of the lever. Bellows nozzle 82 is controlled by a sliding valve 83 which 48. and 49 are both subjected on their outsides controls ports 84 located in a cylinder 85 which to ambient pressure. Bellows 48 and 49 form extends across chambe'r80. Valve 83 isprovided means ‘responsive to the pressure in the cabin with a stem 86 which projects out through wall" which means. controls motorv 32 to effect adjust 20 19 and is connected to the movable end of- a cor ment of valves 2| and 21. On motor shaft 3| is rugated bellows 81 supported in a housing cap 88. an arm .53 which operates the limit-switches 39 Corrugated bellows 81 is evacuated and is pro and 48. To give width of regulation-to bellows vided on its inside with a compression spring 89 48 and 49 so as to obtain stable .operation of which acts in a direction to distend the bellows. the control mechanism, there is provided a spring 25 The interior of cap 88 is‘ connected to atmosphere 54 which at one end is connected to lever 45 and through one or more openings 90. Thus, corm at the other end is connected to an arm 55 piv gated bellows 18 is subjected onits outside to oted' on a ?xed support58 and having its other ambient ‘pressure and, as the ambient pressure ' end provided with a notch which engages a pin decreases, sliding valve 83 is moved toward a po- _ 51 carried by gear 30. Thus turning of gear 38 30 sition wherein it covers ports 84. When ports 84 to adjust valves 2| and 21 serves also to adjust are covered, ?ow of supercharged air to the the tension of spring 54. At 58 and 59 (see Fig. ejector nozzle 82 is cut off, thus putting the .3) are adjustable stops for limiting turning move- _ ,ment of lever 45. ejector out of operation. ' ' Over the discharge end of conduit 1 is a ?ap \ The ?elds l9 and 28 of motor |8 are connected 35 valve 9| pivoted on a pin 92 and biased toward through limit switches 68 and GI and relays 62v and 63 .to the ?xed contacts 64 and 85 of a tem perature responsive device located in the cabin closed position by its weight and by a spring 93 (Fig. 3). It serves to prevent back ?ow of air through'conduit '|. ' and responsive to the temperature therein. In Referring to Fig. 1, it will be seen that motor ‘ the present instant, the temperature responsive 40 32 is fastened to the sides of conduits 6 and '| by device is shown as being in the ‘form of a bi-metal suitable straps 94 and that casing 41 which strip 88 ?xed at one end 61 and provided with a contact 68 at its other end adapted to engage ?xed ‘contacts 84 and 65. Connected with link 31 is a pivoted arm 69 which functions to operate the limit switches 60 and GI. Arm 69 is pivoted houses bellows 48 and 49 and associated parts likewise is fastened on the sides of these con on a ?xed support as indicated at 18 and is con Rheostat l3 iscarried by a bracket 95 Thus the entire mechanism is a unitary structure which is attached to the cabin well through the intermediary of the three nected to link 31 by a suitable pivotal connection as indicated at ‘H (see Fig. 3). To give width of regulation to the temperature responsive device conduits ||, l2 and 15. In Fig. 2 of the drawings, the various parts are shown in the positions they might occupy with so as to eifect‘stable operation, there is provided in connection with ‘it an electromagnet 12 the the aircraft on the ground and the ejector not armature of which is attached to bi-metal strip 66. The Winding of electromagnet '|2 isin cir duits. '- attached to flange 5. operating, the cabin being open to atmosphere Valves 2|, 2'! and 91 are shown ‘ ‘for example. closed and valves l4 and 28 are shown in positions cuit with a rheostat 13, the operating arm 14 of ' they might occupy at some certain temperature which is attached to shaft 35. Operating arm 14 is moved along with valves l4 and 28 to vary the amount of resistance in circuit with the winding of electromagnet ‘l2 asthe valves are adjusted, sealed and the ejector is put into operation, the ejector will function to partially open valves 21 and 9| and effect flow of air through the cabin thus varying the strength of the electromagnet and hence its effect on the thermostatic bimetal strip. ‘ Flow of air from the cabin is through a conduit _ 15 which leads to an air chamber 18 formed by in the cabin. However, as soon as the cabin is _for ventilating the cabin while the aircraft is on - the ground, is taxiing, or is at low altitude, as‘ will be clear from the following description. , As soon as the cabin is sealed and air supplied to the ejector, the ejector functions to‘ pump‘ air walls 11 which in turn are bolted to the side of " from the cabin thus lowering the pressure in the casing 2 and form a part of one side wall thereof. Projecting from the one wall ‘I1 is a discharge nozzle 18 which extends across the mixing cham cabin which'means that the pressure supplied to the interior of bellows 48 is decreased. At this time, sliding valve 83 is open and since the air craft power plant. is operating, compressed air is supplied to the ejector. ‘ ‘Decrease of the pressure in bellows 48 will ef fect movement of lever 45 to bring the movable contact 44 of vacuum switch 43 into engagement‘ with'?xed contact 4|, thus closing a circuit on ber formed by easing 2 and projects out beyond casing 2 to communicate with atmosphere. This is best shown in Fig. 3. In the diagrammatic showing in Fig. ‘2, these ports are shown sepa~ .rated from Casing 2 for purposes of illustration. Thus air from the cabin 'may ?ow through con duit 15 to chamber 18 and thence through nozzle 75 ?eld 33 of motor 32, effecting operation of the _ 2,412,071 i ‘ 5 effect stable operation. ' When the valves H and motor in a direction to move valves2| and'21 ' - 28 are moved in one direction or the .other, the toward open positions. The valves 2| and 21 will assume positions such that there is supplied through conduit 1 or through conduits 8 and 1 air of a pressure to restore lever 45 to its position of equilibrium wherein movable contact 44 stands amount of resistance in series with the'winding of electromagnet 12 is increased or decreased, thus varying its‘ effect on the thermostatic ele ment. This is a known arrangemena It forms no part of our present invention. Any suitable between ?x'ed contacts “and 42. Depending on - arrangement for giving droop to the thermostatic operating conditions, this may boa-position in regulator to effect stable operation may be uti which valve 2| is still closed and 'valve 21 is partly open or one in which both valves 2| and 21 are 10 partly open. The pressure of the air ?owing in conduit ‘I will be su?icient to hold valve 8| open. lized. ' ' In connection with the operation at lower alti tudes, the supercharged air supplied through con duit 8, in a case where the air is being supplied of the valves 2| and 21, the tension of spring 54 ' from the discharge side of the compressor of a . is adjusted to increase its pull on lever 45 which 15 gas turbine power plant, may have a tempera ture of the order of 250° F. and a pressure of means that to restore lever 45 to a position 1 the order of 60 pounds per square inch absolute. wherein movable contact 44 is moved out of en And the air supplied through conduit I0 may gagement with ?xed contact 4|, the pressure in have a‘pressure a few pounds higher than at- ' the cabin, i. e., in' bellows 48', need not be re stored to its former value but tow-a value some 20 mospheric pressure and a temperature substan tially equal to'ambient temperature. In the cab. what less‘ than its former value. Thus, there is in, it may be desired to hold a. pressure equal to introduced into the control a droop to give sta ambient pressure less a predetermined amount bility of operation. This condition of voperation ‘up to a certain altitude after which it may be will obtain while the aircraft is on the ground desirable to hold a pressure for each altitude a and is taxiing, thus insuring ventilation of the When gear wheel 30 moves to effect movement _ cabin at these times. predetermined amount higher than ambient pres- , ' sure. As to temperature, it may be desirable to decrease the cabin temperature with increase in Now when the aircraft gets under way and .gains altitude, the pressure responsive device will . altitude. The desired results may be obtained operate after the manner described to adjust valves 21 and 2| to maintain the desired cabin 30 by selecting suitable ‘characteristics for the con trol members. _ ' pressure. After the aircraft gets under way, At lower altitudes, and as long as flap valve 8| rimmed air becomes available through conduit is open, the temperature control is effected pri marily due to the adjustment of valve 28. At The temperature responsive device in the cabin operates to position valves l4 and 28 to effect ' lower altitudes, the cooler I3 has but limited ef fect on the temperature of the air ?owing through regulation of the cabin temperature. Valve 28 it so that the exact position of valve l4 and the affects the rateof ?ow of air through conduit 1. division of the air between the two conduits -II If the temperature is too low in the cabin, ther ' mostatic member 56 willbe moved to engage con 'tact 65 to effect operation of motor I8 to move valve 28 toward closed position to reduce the ?ow through conduit 1 and to move valve l4 down ward (as- shown in Fig. 2)' to decrease the ?ow through conduit l2 and cooler l3 and increase the flow through conduit ||. Decreasing the ?ow through conduit ‘I by closing valve 28 somewhat serves to reduce the pressure in mixing chamber and I2 is not of major importance. 40 2 and such reduction in pressure serves to effect - ‘ As the aircraft ascends, an altitude is reached at which flap valve 9| is closed, the cold rammed air having no longer su?lcient pressure tohold it open. ‘When this occurs, all the air for super charging the cabin is supplied through conduit 9 from the hot supercharged air supply. With ?ap valve 9| closed, valves 21 and 28in conduit 1 no longer have any effect on the air ?ow. The pressure and temperature of the air is then con ' trolled by the two valves 2| and HI, valve2| operating to increase and decrease the supply adjustment of valves 2| and 21 in the manner already explained ‘in an opening direction. Thus, valve 2| is opened to admit a greater amount of. , of supercharged air to the mixing chamber and valve |4 operating to effect a division of air be hot air to increase the temperature. ___At the same tween the two conduits H and I2 sot'that the air . time, the pressure in mixing chamber 2 is re supplied to the cabin will have the desired stored. If the temperature in the cabin is too temperature. At these higher altitudes,‘ the am high, thermostatic member 86 engages ?xed con bient temperature is lower and therefore cooler tact 64' to effect operation of motor l8 and the |3 has a greater effect on the temperature of the adjustment of valves l4 and 28 in the opposite directions. This then results in an increase in ‘ air ?owing through it. At-lower altitudes, the; difference in pressure ‘ pressure in mixing chamber 2 which in turn efbetween the-inside and outside of the cabin is til fects a readjustment of valves 2| and 21 in the opposite direction to decrease the pressure and hence decrease the temperature. , . There results that for any altitude, valves 2| relatively small so that‘ the ejector is'needed to effect circulation of air through the cabin. Howe ever, as the altitude increases, the‘di?erence in pressure between the inside and outside of the to supply tothe cabin air of the desired pressure 05 cabin increases‘ so that less and less ejector ‘ac tion is needed to effect circulation through the and temperature and such pressure. and.tem - and 21 and valves l4 and 28\become positioned perature will be held by readjustment of the valves. It will be understood that if the pressure in the mixing chamber decreases, an operation similar to that already described in connection," with an increase in pressure will effect opera tion of motor 32 in a direction to move valves 2| , and 21 toward open positions. 13 is to give a droop- . - cabin. The function of valve 83 is to begin to decrease the ejector action after a predetermined altitude is reached and ?nally at some altitude cut the ejector o?altogethe'r. The bellows 81 connected to ejector valve 83 and its spring 89 . have characteristics such that after a predeter mined altitude is reached, the bellows begins to disténd; due to decrease in ambient pressure, thus The function of resistance moving valve 83 toward closed position." The ing characteristic to the thermostatic control to 75 2,412,071 7 8 valve is moved gradually toward closed position‘ the other end by a link L05 to the temperature , with increase‘ in altitude and eventually at some control mechanism. desiredaltitude, the valve is entirely closed thus shutting oftthe ejector. The circulation of air through the cabinis now effected by the ?ow of airthrough conduit ‘15 and nozzle 18 due to dif-' ierence in'pressure between the inside and out side of the cabin. , , In accordance with the provisions of the pat ent statutes, We have described the principle of operation of our invention, together with the apparatus which we now consider to represent the best embodiment thereof, but we desire to have it understood that the apparatus shown is only illustrative and that the invention may be Nozzle 18 may have the ca pacity and be so designed ‘thatfor the intended ‘ altitudes, the How through the cabin after the 10 carried out by other means. ’ ejector is shut oil will be satlsfactory'for venti What we claim as new and desire to secure by lating purposes and at the highest altitude will Letters Patent of the United States, is: not be excessive. Also, the ~ejector functions to 1. In a cabin-superchargersystem, the com ventilate the cabin while the aircraft is on the bination of an air mixing chamber, a ?rst'dis ground, particularly while taxiing, since at this 15' charge conduit connecting the mixing chamber time sui?cient air from the propeller slip stream to the cabin, a second discharge conduit connect is not available. While I now prefer to utilize - ing the, mixing chamber to the cabin, an air an ejector as described, it will be understood that cooler in the second conduit, valve means‘ for ap if desirable an ejector-may be omitted. ~ portioning flow of air from the mixing chamber It will be noted that the cabin discharge noz v20 to said two conduits, a ?rst supply conduit for 'zle 18 extends ‘across the mixing chamber 2 so that it is surrounded by warm air. This serves supplying hot supercharged air to the mixing chamber, a second supply conduit for supplying to prevent frosting of ‘the nozzle. . rammed air to the mixing chamber,- a valve in As stated above, the pressure and temperature each supply conduit, means responsive to cabin control devices may be selected and adjusted to 25 pressure for adjusting said two valves, a second have characteristics such that they maintain the valve in said second supply conduit, and means desired cabin pressures and temperatures for the responsive to cabin temperature for adjusting said altitude range ‘of the aircraft. In the case of secondvalve and said valve means. the pressure control device, at lower altitudes 2. In a cabin supercharger system, the com the control is effected by bellows 48 alone or 30 bination of an air mixing chamber, a ?rst dis modi?ed by spring 54. At a predetermined alti charge conduit connecting the -mixing chamber tude, ambient pressure reaches a low- value such to the cabin, a second/discharge conduit connect that bellows 49 distends to a point where its mov ing the mixing chamber to the cabin, an air cooler able end engages lever 45. It then serves to af in the second conduit, valve means vfor apportion fect the control device by an amount dependent ing ?ow of air from the mixing chamber to said upon the altitude, the'force acting on lever 45 two conduits, a ?rst supply conduit for supply being that of bellows 48 as modi?ed by spring ing hot supercharged air to the mixing chamber, , 54 and bellows 49. By way of example, but not a second supply conduit for supplying rammed air ' by way of limitation of our invention, the pres sure control device may have characteristics such that after takeo? and below an altitude of about 15,000 feet; the regulator will maintain the cabin pressure at one-fourth to three-fourths pounds, per square inchabove ambient pressure; and to the mixing chamber, a valve in each supply conduit, means responsive'to cabin pressure for adjusting said two valves, the valve in said sec ond supply conduit being partly opened in ad vance of the valve in said first supply conduit, cabin temperature responsive means, and means above 15,000 feet altitude, at which time bel 45 including said valve means adjusted by said tem lows 49 may come into action, the regulator will perature responsive means to regulate the tem perature in the cabin. maintain the cabin pressure at one-half ambient pressure plus 5' pounds. This means a continu 3. In a cabin supercharger system, the com ously decreasing cabin pressure with increase in bination of a mixing‘ chamber, a pipe for convey altitude. However, if desired, constant or sub 50 ing air from the mixing chamber to the cabin, stantially constant cabin pressure may bemain a ?rst conduit for supplying hot pressurized air to the‘ mixing chamber, a second conduit for sup tained. ‘ . Suitable manual means may be provided for adjusting the setting of the thermostat as is well understood. ' - plying rammed air to-the mixing chamber, valve - means for regulating the ?ow through the sec 55 ond conduit, means responsive to cabin pressure Valve 24 is in the nature of an emergency valve which may be closed to shut off all hot air, a _ thing which, at higher altitudes when ?ap valve and to cabin temperature‘ for positioning said valve means, other valvemeans for regulating the ?ow through the ?rst conduit and means re BI is ,closed, would put the entire system out of operation. Its operating means 25 may bev lo cated at any suitable point where itvis readily sponsive to cabin pressure for positioning said 60 other valve means. , . ' ‘ 4. In a, c..'oin supercharger system, the com bination of a mixing chamber, a ?rst pipe for con ' veying air from the mixing chamber to the cabin, accessible to the‘ aircraft operator. ‘Referring to valves 21 and 28 which control "flow through conduit 1, it will be seen that they a second pipe for conveying air from the mixing vmutually cooperate in regulating such flow and 65 chamber to the cabin, a heat exchanger in one in substance form a single valve means positioned by cabin pressure and temperature. If found desirable, a single valve may be used instead of the two valves 2‘! and". Such a modi?cation is shown in Fig. 4 wherein I00 indicates acon duit corresponding to conduit ‘I of Figs. 1 to 3 in which is located a single valve |0l connected by a link I02 to an intermediate point of a ?oat of ‘ said. pipes, valve means in the mixing cham ber for apportioning ?ow of air from the mix ing chamber through said two pipes to the cabin, ' a ?rst conduit for supplying hotpressurized air, to 70 the mixing chamber, a second conduit for sup plying rammed air‘ to the mixingchamber, valve means in said conduits, means-responsive to cabin pressure for positioning the valve means in said ing lever I03 one end of which is connected by a ‘ ?rst conduit, and means responsive to cabin tem link I04 to the pressure control mechanism and 75 perature for positioning the valve means in saidv ‘ 2,412,971 . 9 I . ’ by cabin temperature for regulating the cool- ' ing e?ect of said cooling means on the air ?owing through said conduit means to the cabin. 10. In ‘a cabin supercharger system, a sealed second conduit and the valve means in the mix ing chamber. _ , 5. In a cabin supercharger system,»the ,com bination of a mixing chamber, ‘a, ?rst pipe for conveying air from the mixing chamber to the cabin, a second pipe for conveying air from the mixing chamber to the cabin, a heat exchanger cabin, a mixing chamber, ?rst conduit means including air cooling means, for conveying air from the mixing chamber to the cabin, second conduit'means for conveying hotsupercharged air in one or said pipes, valve means in the mixing ~ chamber for apportioning ?ow of air from the to said mixing chamber, third conduit means for cabin, a ?rst conduit for supplying hot pressurized automatic’ valve means associated with said sec mixing chamber through said two pipes to the 10 conveying rammed air to said mixing chamber, ond and third conduit means and ‘actuated by a ' _ air to the mixing chamber, a second conduit for device responsive to cabin pressure for modiiy- .. - ing the ?ow to the mixing chamberot both super , means responsive to cabin-pressure for position- 15 charged air and rammed air, and automatic valve means associated withsaid ?rst and third ‘ ing said last-named valve means, means respon supplying rammed air to the mixing chamber, valve means in said‘?rst and second conduits, conduit means and actuated by a device respon sive' to cabin temperature for modifying the ?ow. sive to cabin temperature for positioning both the valve means in said second conduit and said valve .rneans in the mixing chamber, and a check . oi rammed air to the mixing chamber and regu the cooling e?ect of said cooling means on valve for preventing back ?ow through said 20 lating the air ?owing through said ?rst named conduit rammed air supply conduit._ 6. In a cabin supercharger system, _ a sealed means. -' » - . 11. In. a cabin supercharger system, a sealed cabin,- means for supplying supercharged air to the cabin, means responsive to cabin pressure and cabin, a mixing chamber, conduits for supplying to cabin temperature ‘for regulating said air sup plying means, a conduit communicating with the cabin, an ejector in said conduit for eiiecting flow of air through ‘said sealed cabin, a conduit for supplying supercharged air from the ‘supply said mixing chamber, conduit means for convey ing air from the mixing chamber to the cabin, cabin pressure and cabin temperature responsive means to: regulating the air ?ow in said conduits, ‘ means to the ejector for the actuation air of diiierent ' pressures and ‘ temperatures to and means ‘for discharging air from the cabin thereoi so including a nozzle arranged in heat exchange re and means associated with said last-named con lation with the mixing chamber so as to prevent ‘ ting o? the supply of supercharged air to said _ frosting oi the nozzle. 12. In a cabin supercharger system, a sealed ejector when a predetermined altitude is reached. 7. In a cabin supercharger system, a sealed 35 cabin, a mixing chamber, conduits for supply ing air of di?erent pressures and temperatures cabin, means for supplying supercharged air to to said mixing chamber, conduit means for con the cabin, means responsive to cabin pressure veying air rrom the mixing chamber to thecabin, ' duit and responsive to altitude pressure for shut and to cabin temperature .for regulating said - cabin pressure and cabin temperature respon air supplying means, a ‘conduit communicating sive means for regulating‘ the air flow in said with the cabin, an ejector in said conduit for ei 40 _ conduits, means for dischargingair from the ‘ tecting ?ow of air through said sealed Tcabin, a cabin including a nozzle arranged in heat e'x-, conduit for supplying supercharged air from the change relation with the mixing chamber so as supply means to the ejector for theactuation to prevent frosting oi the nozzle, and ejector thereof, and means associated with said last named conduit and responsive to altitude’ pres - means-tor e?ecting ?ow oi.’ air through the cabin and out said discharge nozzl . sure for gradually shutting oi! the supply of supercharged air to said ejector. . 13..In a cabin supercharging system, a sealed v cabin, a mixing ‘chamber, a source of hot super 8. In a cabin supercharger system,- conduit a means includirm air cooling means and a' mixing -‘ charged air, ?rst conduit means connecting the chamber for conveying air to the cabin, a pipe 50 hot air source to the mixing chamber, a source of cold rammed air, second conduit means con ‘for supplying hot supercharged air to the mixing necting thecold air source to the mixing cham I chamber, a pipe for supplying rammed air .to the ber, third conduitmeans connecting the‘mixing mixing chamber, valve means in said pipes, means chamber to the. cabin and including .air cooling responsive to cabin pressure for positioning said' valve means, and means responsive to cabin tem perature for regulating the cooling e?ect of said 55 air cooling means on the air ?owing to the cabin. 9. In a cabin supercharger system, a ‘sealed cabin, a mixing chamber, conduit means inolud» ‘ing air cooling means for conveying air from the‘ so mixing chamber to the cabin, a ?rst pipe for con veying hot supercharged air to the mixing cham diet‘, a second pipe for conveying rammed air 'to the mixing chamber, valve means in said pipes, means, a‘ ?rst control mechanism responsive to cabin pressure, a second control mechanism re-‘ sponsive .tolcabin temperature, valve means asso ciated with said ?rst conduit means and posi tioned by said ?rst control mechanism for regu lating the now of pressurized air, valve means associated with said second conduitvmeans' and positioned by said second control mechanism ior regulating the ?ow of cold air to the mixins chamber, and third. ‘v ‘ve means positioned by ‘an actuating device “1' said "1“- meal'ns cm‘ ii?v’said second control mechanism for regulating the - trolled by-cabin pressure, other valve means in :3 wcoolmgmem_ said second pipe, an actuating device for said J} other valve means controlled by cabin tempera- “ ture, and condition-responsive means controlled - norms) r. WARNER. _ near. 1.. AUYER. '