GB2495312A - Central Injection Opposed Piston Combustion Chamber - Google Patents

Central Injection Opposed Piston Combustion Chamber Download PDF

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Publication number
GB2495312A
GB2495312A GB201117205A GB201117205A GB2495312A GB 2495312 A GB2495312 A GB 2495312A GB 201117205 A GB201117205 A GB 201117205A GB 201117205 A GB201117205 A GB 201117205A GB 2495312 A GB2495312 A GB 2495312A
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GB
United Kingdom
Prior art keywords
piston
toroid
combustion chamber
text
toroidal
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.)
Granted
Application number
GB201117205A
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GB2495312B (en
GB201117205D0 (en
Inventor
Henry William Bonner
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Individual
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Individual
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Publication date
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Priority to GB201117205A priority Critical patent/GB2495312B/en
Publication of GB201117205D0 publication Critical patent/GB201117205D0/en
Publication of GB2495312A publication Critical patent/GB2495312A/en
Application granted granted Critical
Publication of GB2495312B publication Critical patent/GB2495312B/en
Expired - Fee Related legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B75/00—Other engines
    • F02B75/28—Engines with two or more pistons reciprocating within same cylinder or within essentially coaxial cylinders
    • F02B75/282—Engines with two or more pistons reciprocating within same cylinder or within essentially coaxial cylinders the pistons having equal strokes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B3/00—Engines characterised by air compression and subsequent fuel addition
    • F02B3/06—Engines characterised by air compression and subsequent fuel addition with compression ignition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B75/00—Other engines
    • F02B75/28—Engines with two or more pistons reciprocating within same cylinder or within essentially coaxial cylinders
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
    • F02F3/00—Pistons 
    • F02F3/26—Pistons  having combustion chamber in piston head
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B75/00—Other engines
    • F02B75/02—Engines characterised by their cycles, e.g. six-stroke
    • F02B2075/022—Engines characterised by their cycles, e.g. six-stroke having less than six strokes per cycle
    • F02B2075/025—Engines characterised by their cycles, e.g. six-stroke having less than six strokes per cycle two

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

An opposed piston axial flow two stroke compression ignition engine having a combustion chamber comprising three quadrants of a toroid 8 formed in one piston 6, with a centrally mounted outward firing injector 3 aligned as closely as possible with the central plane of the toroid, such that the line of injection of the fuel 4 strikes the outer wall of the toroid at the diameter and below the overhanging crown. The fourth quadrant 9 of the toroid is formed in the opposing piston 7. The piston crowns are tangential to the toroidal section, such as to create a toroidal vortex as the incoming air is compressed between the piston crowns.

Description

CENTRAL INJECTION OPPOSED PISTON COMBUSTION CHAMBER
This invention relates to an opposed piston axial flow two stroke compression ignition engine, with a centrally mounted injector.
Such a system might incorporate an injector with multiple nozzles injecting radially into a combustion volume. See Figure 1.
The DISADVANTAGES with this system are as follows:- 1. A high degree of swirl must be induced into the incoming air. The rotation of the charge will thee be accelerated as it is compressed into the inner combustion volume, by the principle of conservation of angular momentum.
2. Efficient cpmbustion will be dependent upon the injector producing a wide spray pattern in which the Ibel is effectively atomized. The miniscule particles of fUel can then combust with the fresh oxygen molecules as they sweep past tangentially relative to the cylinder centreline.
I However, if the spray pattern is too wide, the penetration of the fUel will be insufficient to fUlly mix with the incoming air.
4. But if the spray pattern is too narrow, or even a jet, the fUel will continue clean past the toroidal volume unopposed by the inflow of air as the pistons approach each other. It will then reach the cylinder wall as liquid fUel and be unable to mix or combust with the air.
5. The geometry of the combustion chamber is continually changing, and even if conditions are developed to the point of being ideal at any one moment, it would be very difficult to maintain that situation throughout the injection period.
STATEMENT of INVENTION
To overcome this, the present invention proposes a combustion chamber comprising three quadrants of a toroid formed in one piston. The injector is lined up axially to fire as closely as possible at the centre of section of the partial toroid formed in this piston. Closure of the combustion chamber is effected by a fourth quadrant of the toroid formed in the contra piston.
The ADVANTAGES of this system are as follows:- 1. Over the injection period the geometry of the combustion chamber alters little.
2. As the piston and contra piston approach TDC, the airflow will become toroidal about the centre of section of the toroid, and rotational about the centreline of the cylinder.
3. The injector is firing at the diametrically opposite wall of the combustion chamber throughout the injection period.
4. The exact spray pattern from the injector is less critical. If it is narrow or ajet and reaches the far side of the toroid in liquid form, it will ricochet off the far wall as an atomized spray.
5. If the spray pattern is wider, and penetration is reduced, the incoming air will still be flowing past the spray as it is injected, and efficient combustion will still take place.
6. The complexity of the airflow will further ensure efficient combustion with the atomized fijel 7. This arrangement prevents any unburnt liquid fuel travelling outside the toroidal combustion chamber, and provide for complete combustion within the chamber.
INTRODUCTION to DRAWiNGS
Figure 1 shows a combustion chamber where fuel (4) from injector (3) can readily escape from the chamber between the crown of piston (1) and piston (2), and reach the cylinder wall (5). Geometry is rapidly changing and air movement normal to the line of injection is not assured.
Figure 2 shows a typical example of the present invention.
Figure 3 shows how the fuel spray pattern relates to the toroidal air flow.
Figure 4 shows how the fuel spray pattern relates to the axial rotation of the air.
DETAILED DESCRIPTION
Use Figure 2 A combustion chamber comprising three quadrants of a toroid (8) contained within piston (6). An injector (3) so positioned axially that its line of fire is equispaced about the diameter of the toroid over the injection period.
Use Figure 3 Toroidal air flow (10) traverses the outward path of fUel spray (4), and also the inward path in the event of the jet reaching the outer wall and ricocheting back.
Use Figure 4 Preferably, there will be swirl induced as the air enters the cylinder, the rotational velocity of which is amplified according to the reduction of radius of gyration on compression into the combustion chamber. In this ease air flow (11) traverses the outward path of fUel spray (4), and also the inward path in the event of the jet reaching the outer wall and ricocheting back.
Use Figure 2 A combustion chamber comprising three quadrants of a toroid formed in one piston, with an outward firing injector aligned as closely as possible with the central plane of the toroid, such that the line of injection strikes the outer wall of the toroid at the diameter and below the overhanging crown. The fourth quadrant of the toroid is formed in the opposing piston.
The piston crowns are tangential to the toroidal section, such as to create a toroidal vortex as the incoming air is compressed between the piston crowns.

Claims (1)

  1. <claim-text>CLAIMS1. A toroidal combustion chamber, the majol part of which is formed in the crown of one piston, such that the centre of the toroid lies below the crown which thus overhangs the central plane, a central injector with an outward path of injection in the central plane to strike the outer diameter of the toroid below the overhanging crown, the remainder of the toroidal section to be formed in a second opposing piston such as to complete the toroid on closure.</claim-text> <claim-text>2. A toroidal combustion chamber as in claim 1, where the piston crowns are tangential to the toroidal section.</claim-text> <claim-text>3. A toroidal combustion chamber as in claim 2, where the piston crowns are at right angles the cylinder axis.</claim-text> <claim-text>4. A toroidal combustion chamber as in claim 2, where the piston crowns are not square to the cylinder.</claim-text>
GB201117205A 2011-10-05 2011-10-05 Central injection opposed piston combustion chamber Expired - Fee Related GB2495312B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB201117205A GB2495312B (en) 2011-10-05 2011-10-05 Central injection opposed piston combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB201117205A GB2495312B (en) 2011-10-05 2011-10-05 Central injection opposed piston combustion chamber

Publications (3)

Publication Number Publication Date
GB201117205D0 GB201117205D0 (en) 2011-11-16
GB2495312A true GB2495312A (en) 2013-04-10
GB2495312B GB2495312B (en) 2014-02-19

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
GB201117205A Expired - Fee Related GB2495312B (en) 2011-10-05 2011-10-05 Central injection opposed piston combustion chamber

Country Status (1)

Country Link
GB (1) GB2495312B (en)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB531366A (en) * 1939-07-20 1941-01-02 Herbert Frank Percy Purday Improvements relating to the combustion chambers and fuel supply thereto in two-stroke compression ignition oil engines
US6182619B1 (en) * 1998-12-24 2001-02-06 General Atomics Aeronautical Systems, Inc. Two-stroke diesel engine
US20090025681A1 (en) * 2005-04-19 2009-01-29 Takeshi Takahashi Direct Injection Diesel Engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB531366A (en) * 1939-07-20 1941-01-02 Herbert Frank Percy Purday Improvements relating to the combustion chambers and fuel supply thereto in two-stroke compression ignition oil engines
US6182619B1 (en) * 1998-12-24 2001-02-06 General Atomics Aeronautical Systems, Inc. Two-stroke diesel engine
US20090025681A1 (en) * 2005-04-19 2009-01-29 Takeshi Takahashi Direct Injection Diesel Engine

Also Published As

Publication number Publication date
GB2495312B (en) 2014-02-19
GB201117205D0 (en) 2011-11-16

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Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 20201005