US1620565A - Explosive chamber for gas engines - Google Patents
Explosive chamber for gas engines Download PDFInfo
- Publication number
- US1620565A US1620565A US665922A US66592223A US1620565A US 1620565 A US1620565 A US 1620565A US 665922 A US665922 A US 665922A US 66592223 A US66592223 A US 66592223A US 1620565 A US1620565 A US 1620565A
- Authority
- US
- United States
- Prior art keywords
- sleeve
- piston
- chamber
- explosive chamber
- charge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R7/00—Intermittent or explosive combustion chambers
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S60/00—Power plants
- Y10S60/91—Free piston
Definitions
- the present invention relates to new and useful improvements in motors. and it pertains more'particularly to turbines of the impact type.
- lt is one of the primary objects of the present invention to provide a new and improved form of explosive chamber adapted to generate power for use in connection with impact turbines.
- lt' is a further object ot the invention to construct a chamberot this type in which a gaseous fuel is tired under pressure and exhausted from the chamber.
- lit is a further object of the invention to provide an explosive chamber of the type above described, which will receive a gaseous fuel under pressure, ignite the same, and discharge the products ot combustion in the presence ot a rotor of the impact type.
- lt is a further object ot t e invention to provide a chamber which Willcarr'v out the aforementioned operations automatically.
- Figure 1 is a view in elevation, partly in section, showing an explosive chamber constructed in accordance ⁇ With the present invention and oneiform of attachment to an impact turbine;
- Fig. 2 is a longitudinal sectional view ot the explosive chamber With its parts in a position opposite to the position in -which thev are shown in ldig. 1;
- ig. 3 is a vertical sectional view taken on the line 3-3 oi Fig. 9L.
- the reiterence numeral 5 designates a turbine ci the impact type, such turbine having a rotor 6 carried by a shaft 7, all of which are ot conventional iorm. Leading into the housing ot the turbine 5 are two in- ,r take passages 8 and 9.
- rEhe reference numeral l0 designates the explosive chamber, which is preferably circular in :torni and has in its side Walls two exhaust passages l1 and which coincide with the inlet passages 8 and 9 hereto-tore referred to.
- 'lhe explosive chamber 10 is preferably formed with rcn'iovable heads 13 and 11iand mounted in the heads 13 and 14, are igniting devices 15 and 16, respectively.
- the chamber is -from the induction coil to the terminal l0 E@ provided with intake passages 16 and 17, and having communication with such intake passages 16 and 17, there is an intake mani- 'fold 18, connected to a suitable source ot fuel supply.
- a sleeve 19 Mounted within the chamber 10, there is a sleeve 19, having tianged ends 20 and 21. 'llhe side Walls ot the sleeve are provided near each end with a circular series ot openings 22, the purpose ot which will be hereinafter described.
- a traveling piston 23 Mounted Within the sleeve 19, there is .a traveling piston 23, and such piston is provided with ports 24 and y25 therein, the port 24 discharging through an opening '26, and the port 25 dischargiuigy through an opening 27.
- the reference numeral 35 designates a suitable source ot power
- 36 designates an induction coil.
- 39 designates a conductor leading of the switch member 31 heretofore mentioned, and leading from the switch member 31 there is a conductor 41 which is connected at its other end to the igniting device 15 carried by the head i3 ot the chamber 10.
- 1HEhe device operates in tbe tollewimn ner: lll/lith the i., arts in positie" in l, en explosive c arge uncleL sure is admitted by Way o ,he intalre fold it, port il', port 25 in tbe pi. t and opening il?, to the space bettree piston 23 and. the head la the cha Ils this charge under pressure is te the piston is to the ric..
- a Q0 et the sleeve la. tales place, the sleeve 19 moved t ,e right, in which position it is ovvn in Q. Simultaneously with this movement, the piston 23 engages the sliding gin f2@ and the litt
- the present invention provides means whereby ex losive charges are intermittently presente to the rotor ofthe turbine .to drive headset the saine, and that after the device has been started the same is automatic in its operation and will continue to supply the turbme with products of combustion under pressure until the supply oir' fuel has been cut off.
- a power impulse generator comprising a cylinder having an inlet and an outlet port at each end thereof, a sleeve movable within said cylinder, said sleeve having a plurality of openings. passing through its side wall at a point near each end of the sleeve, a piston freely movable Within the sleeve and serving to reciprocate said sleeve iu response tothe pressure of each fuel charge entering said cylinder, said piston.
- a piston freely movable within the sleeve and serving to reciprocate said sleeve in response to the pressure of each fuel charge entering said cylinder, said piston having a plurality of passages adapted respectively to register with the inlet ports of the cylinder and the openings in the ends of the sleeve to establish communication between the inlet ports and the interior of said cylinder, and means operating in conjunction with the inlet and outlet ports, the openings in the sleeve and the passages in the piston for causing successive explosions for the purpose specified.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Description
' 1,620,565 March 8, 1927- J B, MCKEOWN EXPLOSIVE CHAMBER FOR GAS ENGINES QM@ l M A TTOR NE YS arch 8 7 J. B. MCKEOWN EXPLOSIVE CHAMBER FOR GAS ENGINES 2 Sheets-Sheet 2 Filed OCc. l 1923 INVENTOR @N5 'MCKEO WN A TTORNE YS lwatented .ll/[lan til, l2?.
JOSEPH B. MCKEWN, F GBANTWOOD, JERSEY.
EXPLOSVE CHAMBER FOR GAS ENGNES.
Application led (lctobei' 1, 1923. Serial No. 665,925?.
`The present invention relates to new and useful improvements in motors. and it pertains more'particularly to turbines of the impact type.
lt is one of the primary objects of the present invention to provide a new and improved form of explosive chamber adapted to generate power for use in connection with impact turbines. A
lt' is a further object ot the invention to construct a chamberot this type in which a gaseous fuel is tired under pressure and exhausted from the chamber.
lit isa further object of the invention to provide an explosive chamber of the type above described, which will receive a gaseous fuel under pressure, ignite the same, and discharge the products ot combustion in the presence ot a rotor of the impact type.
lt is a further object ot t e invention to provide a chamber which Willcarr'v out the aforementioned operations automatically.
With the above and other objects in view, reference is had to theaccompanying drawings, in Whichv Figure 1 is a view in elevation, partly in section, showing an explosive chamber constructed in accordance `With the present invention and oneiform of attachment to an impact turbine;
Fig. 2 is a longitudinal sectional view ot the explosive chamber With its parts in a position opposite to the position in -which thev are shown in ldig. 1;
ig. 3 is a vertical sectional view taken on the line 3-3 oi Fig. 9L.
Referring more particularly to the drawings, the reiterence numeral 5 designates a turbine ci the impact type, such turbine having a rotor 6 carried by a shaft 7, all of which are ot conventional iorm. Leading into the housing ot the turbine 5 are two in- ,r take passages 8 and 9.
rEhe reference numeral l0 designates the explosive chamber, which is preferably circular in :torni and has in its side Walls two exhaust passages l1 and which coincide with the inlet passages 8 and 9 hereto-tore referred to. 'lhe explosive chamber 10 is preferably formed with rcn'iovable heads 13 and 11iand mounted in the heads 13 and 14, are igniting devices 15 and 16, respectively.,
At points removed :trom the exhaust passages 11 and 12 and preferably diametrically opposed with respect thereto, the chamber is -from the induction coil to the terminal l0 E@ provided with intake passages 16 and 17, and having communication with such intake passages 16 and 17, there is an intake mani- 'fold 18, connected to a suitable source ot fuel supply.
Mounted within the chamber 10, there is a sleeve 19, having tianged ends 20 and 21. 'llhe side Walls ot the sleeve are provided near each end with a circular series ot openings 22, the purpose ot which will be hereinafter described. Mounted Within the sleeve 19, there is .a traveling piston 23, and such piston is provided with ports 24 and y25 therein, the port 24 discharging through an opening '26, and the port 25 dischargiuigy through an opening 27. l
Mounted in the head 13 of the chamber there is a sliding pin 28, carrying a switch member 29, and in the head 14 of the chamber there is a sliding pin 30, carrying' a. switch member 31. rlhe sliding pins are controlled by springs 32 and 33, respectively. The reference numeral 35 designates a suitable source ot power, and 36 designates an induction coil. Leading trom the in-y duction coil 36, there is a conductor 37, which is grounded as at 38. Thereterence numeral 39 designates a conductor leading of the switch member 31 heretofore mentioned, and leading from the switch member 31 there is a conductor 41 which is connected at its other end to the igniting device 15 carried by the head i3 ot the chamber 10. Leading troni the switch member 29 there is a conductor l2 connected, as at 43, to the conductor 39 heretofore mentioned. llieacf ing from the switch member 29, there is conductor fill, and such conductor is eenAw nected to the igniting device itl mounted in the head 1st ot the chamber 10.,
1HEhe device operates in tbe tollewimn ner: lll/lith the i., arts in positie" in l, en explosive c arge uncleL sure is admitted by Way o ,he intalre fold it, port il', port 25 in tbe pi. t and opening il?, to the space bettree piston 23 and. the head la the cha Ils this charge under pressure is te the piston is to the ric.. A Q0 et the sleeve la. tales place, the sleeve 19 moved t ,e right, in which position it is ovvn in Q. Simultaneously with this movement, the piston 23 engages the sliding gin f2@ and the litt
connects, through the medium o1.
29, the conductors 42 and 411. rllhis establishes a circuit to the igniting device 16 and lires the charge contained in the space to the left of the piston in Fig. 2, and this charge passes out through the left-hand open end of said sleeve 19, the exhaust port 12 ci the chamber l0, to the intake passage 9 of the turbine, and into the presence of the rotor 6 thereof, which it serves to drive.
Referring to Fig. 2, it will be noted that immediately this action takes place, a charge is taken in through the intake passage 16', the port 24 of the piston, and by way of the opening 26 of the piston enters the space between the piston 23 and the head 13 of the chamber. rIhis pressure forces the piston to the left in Fig. 2, as soon as the pressure of the ignited charge falls below that of the incoming charge, and as the piston travels to the left, the space on the right thereof will be filled with the incoming charge until the piston engages the flange 21 of the sleeve 19v and moves the same to ,the left in which position it is shown in Fig. 1, thus closing the intake passage 16 and opening thegexhaust passage 11. During this movement, the piston 23 engages the sliding pin 30, and through the medium of the switch member 31, completes a circuit through the conductors 39 and 41 to the ignitin device 15, firing the charge at the right o the piston in Fig. 1, which char e passes outwardly through the righthan -open end of the sleeve 19 and through the passage l1, by way of the intake pipe. 8, to the rotor 6 of the turbine 5 which 1t serves to drive.
By reason of the circular series of openings 22, it is apparent that the sleeve 19 need not be guided in its movement since regardless of circumferential movement of the sleeve, a charge will always be fed inwardly of said sleeve to the proper side of the piston.
From the foregoing it is apparent that the present invention provides means whereby ex losive charges are intermittently presente to the rotor ofthe turbine .to drive headset the saine, and that after the device has been started the same is automatic in its operation and will continue to supply the turbme with products of combustion under pressure until the supply oir' fuel has been cut off.
What is claimed is:
1. A power impulse generator comprising a cylinder having an inlet and an outlet port at each end thereof, a sleeve movable within said cylinder, said sleeve having a plurality of openings. passing through its side wall at a point near each end of the sleeve, a piston freely movable Within the sleeve and serving to reciprocate said sleeve iu response tothe pressure of each fuel charge entering said cylinder, said piston.
of openings passing through its side wall at a point near each end of the sleeve, a piston freely movable within the sleeve and serving to reciprocate said sleeve in response to the pressure of each fuel charge entering said cylinder, said piston having a plurality of passages adapted respectively to register with the inlet ports of the cylinder and the openings in the ends of the sleeve to establish communication between the inlet ports and the interior of said cylinder, and means operating in conjunction with the inlet and outlet ports, the openings in the sleeve and the passages in the piston for causing successive explosions for the purpose specified.
JOSEPH B. MCKEUWN.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US665922A US1620565A (en) | 1923-10-01 | 1923-10-01 | Explosive chamber for gas engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US665922A US1620565A (en) | 1923-10-01 | 1923-10-01 | Explosive chamber for gas engines |
Publications (1)
Publication Number | Publication Date |
---|---|
US1620565A true US1620565A (en) | 1927-03-08 |
Family
ID=24672106
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US665922A Expired - Lifetime US1620565A (en) | 1923-10-01 | 1923-10-01 | Explosive chamber for gas engines |
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US (1) | US1620565A (en) |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2461245A (en) * | 1945-01-30 | 1949-02-08 | United Aircraft Corp | Mounting of collector and freepiston gas generators |
US2825319A (en) * | 1955-04-21 | 1958-03-04 | Herbert W Harrer | Free piston engine-compressor apparatus |
US2938506A (en) * | 1947-02-19 | 1960-05-31 | Walder Dr Hermann | Reciprocating piston engine type gas generator for gas turbines |
US3146765A (en) * | 1955-01-25 | 1964-09-01 | Bush Vannevar | Free piston engine |
US4205528A (en) * | 1978-11-06 | 1980-06-03 | Grow Harlow B | Compression ignition controlled free piston-turbine engine |
US4399654A (en) * | 1982-02-19 | 1983-08-23 | David Constant V | Power plant having a free piston combustion member |
US4561252A (en) * | 1984-03-06 | 1985-12-31 | David Constant V | Free piston external combustion engines |
US4653274A (en) * | 1984-03-06 | 1987-03-31 | David Constant V | Method of controlling a free piston external combustion engine |
US4653273A (en) * | 1984-03-06 | 1987-03-31 | David Constant V | Single free-piston external combustion engine with hydraulic piston detection |
US4662177A (en) * | 1984-03-06 | 1987-05-05 | David Constant V | Double free-piston external combustion engine |
US4665703A (en) * | 1984-03-06 | 1987-05-19 | David Constant V | External combustion engine with air-supported free piston |
GB2502582A (en) * | 2012-05-31 | 2013-12-04 | Khalil Abu Al-Rubb | I.c. engine, eg having free piston, with internal or external impeller/turbine |
EP3062023A1 (en) * | 2015-02-20 | 2016-08-31 | Rolls-Royce North American Technologies, Inc. | Wave rotor with piston assembly |
-
1923
- 1923-10-01 US US665922A patent/US1620565A/en not_active Expired - Lifetime
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2461245A (en) * | 1945-01-30 | 1949-02-08 | United Aircraft Corp | Mounting of collector and freepiston gas generators |
US2938506A (en) * | 1947-02-19 | 1960-05-31 | Walder Dr Hermann | Reciprocating piston engine type gas generator for gas turbines |
US3146765A (en) * | 1955-01-25 | 1964-09-01 | Bush Vannevar | Free piston engine |
US2825319A (en) * | 1955-04-21 | 1958-03-04 | Herbert W Harrer | Free piston engine-compressor apparatus |
US4205528A (en) * | 1978-11-06 | 1980-06-03 | Grow Harlow B | Compression ignition controlled free piston-turbine engine |
US4399654A (en) * | 1982-02-19 | 1983-08-23 | David Constant V | Power plant having a free piston combustion member |
US4665703A (en) * | 1984-03-06 | 1987-05-19 | David Constant V | External combustion engine with air-supported free piston |
US4653274A (en) * | 1984-03-06 | 1987-03-31 | David Constant V | Method of controlling a free piston external combustion engine |
US4653273A (en) * | 1984-03-06 | 1987-03-31 | David Constant V | Single free-piston external combustion engine with hydraulic piston detection |
US4662177A (en) * | 1984-03-06 | 1987-05-05 | David Constant V | Double free-piston external combustion engine |
US4561252A (en) * | 1984-03-06 | 1985-12-31 | David Constant V | Free piston external combustion engines |
WO2013179054A3 (en) * | 2012-05-31 | 2014-03-06 | SMITH, Andrew N P | An internal combustion engine and a method of operating an internal combustion engine |
WO2013179054A2 (en) * | 2012-05-31 | 2013-12-05 | SMITH, Andrew N P | An internal combustion engine and a method of operating an internal combustion engine |
GB2502582A (en) * | 2012-05-31 | 2013-12-04 | Khalil Abu Al-Rubb | I.c. engine, eg having free piston, with internal or external impeller/turbine |
GB2518097A (en) * | 2012-05-31 | 2015-03-11 | Khalil Abu Al-Rubb | An internal combustion engine and a method of operating an internal combustion engine |
US9714607B2 (en) | 2012-05-31 | 2017-07-25 | Khalil Abu Al-Rubb | Internal combustion engine and a method of operating an internal combustion engine |
GB2502582B (en) * | 2012-05-31 | 2017-09-27 | Abu Al-Rubb Khalil | An internal combustion engine and method of operating an internal combustion engine |
GB2518097B (en) * | 2012-05-31 | 2018-07-18 | Khalil Abu Al Rubb | An internal combustion engine and a method of operating an internal combustion engine |
EP3062023A1 (en) * | 2015-02-20 | 2016-08-31 | Rolls-Royce North American Technologies, Inc. | Wave rotor with piston assembly |
US10502131B2 (en) | 2015-02-20 | 2019-12-10 | Rolls-Royce North American Technologies Inc. | Wave rotor with piston assembly |
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