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US20100172757A1 - Indirect drive unit apparatus, system and method - Google Patents

Indirect drive unit apparatus, system and method Download PDF

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Publication number
US20100172757A1
US20100172757A1 US12/349,892 US34989209A US2010172757A1 US 20100172757 A1 US20100172757 A1 US 20100172757A1 US 34989209 A US34989209 A US 34989209A US 2010172757 A1 US2010172757 A1 US 2010172757A1
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United States
Prior art keywords
turbine
power source
indirect drive
drive turbine
indirect
Prior art date
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Abandoned
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US12/349,892
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Dale A. Henderson
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Priority to US12/349,892 priority Critical patent/US20100172757A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/10—Application in ram-jet engines or ram-jet driven vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/329—Application in turbines in gas turbines in helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)

Definitions

  • the present invention relates generally to a novel and unique indirect drive unit apparatus, and a method and system of using same.
  • the present invention relates to to a novel and unique indirect drive unit apparatus which can be used with fluid from a gas- or electrically-driven pump or air from a jet turbine, and a method and system of using same.
  • the present invention provides n indirect drive turbine apparatus, comprising: a power source; an indirect drive turbine driven by fluid flow supplied directly or indirectly by said power source; said indirect drive turbine having a drive shaft, a plurality of stages of turbine blades and stationary stator vanes to redirect said fluid flow from a first stage of said plurality of stages of turbine blades and stator vanes to a second stage of said plurality of stages of turbine blades and stator vanes; and whereby each of said plurality of stages of turbine blades and stator vanes recaptures energy as the fluid circulates through said indirect drive turbine, and each time the energy is recaptured it increases force applied to said drive shaft of said indirect drive turbine.
  • An object of the invention is to use principles used in modern jet engines by recapturing spent energy by routing it through stages of turbine blades that turn a drive shaft, and then through stationary vanes to straighten out the flow to be used again by the next stage.
  • FIG. 1 is a schematic view of a first embodiment of the present invention.
  • FIG. 2 illustrates a perspective view, partially in cross-section, of the indirect drive turbine of FIG. 1 .
  • FIG. 3 is a side elevational view of the indirect drive turbine of FIG. 2 .
  • FIG. 4 is front elevational view of FIG. 3 .
  • FIG. 5 is a cross-sectional view of FIG. 3 .
  • FIG. 6 shows a section taken along the line 6 - 6 in FIG. 3 .
  • an indirect drive unit system and apparatus 10 which includes a gas engine 11 , an exhaust pipe 12 , a high volume pump 13 , a storage tank 14 , an indirect drive turbine 15 , a turbine inlet pipe 16 , a turbine shaft 17 , a turbine exhaust pipe 19 , and a control valve 20 .
  • the exhaust pipe 12 is necessary only if a gas engine is used.
  • the arrows 21 , 22 , 23 , 24 , 25 , 26 and 27 shown in FIGS. 1 and 5 indicate the direction of fluid flow.
  • the size and shape of the turbine inlet pipe 16 will vary depending in part upon the volume of fluid being used.
  • the turbine shaft 17 can be connected at a first end 18 to, for example, a transmission (not shown) or a gear box (not shown) to power any external device (not shown) which requires power.
  • the turbine shaft 17 can also be connected at a second end 31 to run, for example, a generator (not shown) or an alternator (not shown).
  • the size and shape of the turbine exhaust pipe 19 will vary with the size and shape of the turbine inlet pipe 16 .
  • the turbine exhaust pipe 19 will be open to the outside air when the fluid being used is air.
  • the apparatus 10 provides a continuous system wherein the fluid is circulated from the storage tank 14 to the pump 13 , and then trough the indirect drive turbine 15 , and then back to the storage tank 14 .
  • the control valve 20 will control the fluid flow to control or regulate the speed of the indirect drive turbine 15 , with a bypass back to the storage tank 14 .
  • the inlet guide vanes and nose cone 28 which directs the fluid in to the blades and turbine wheels 29 ; the turbine shaft 17 which functions as a drive shaft; the fluid flow 24 , 25 , 26 and 27 ; and the turbine disk and blades 30 .
  • the indirect drive turbine 15 can be used with fluid from a gas- or electrically-driven pump in a sealed system, or with air from a jet turbine or ram air from vehicle movement in a open-air system.
  • Forcing air or another fluid through a stage of turbine blades and stator vanes constitutes a first stage.
  • Each stage will recapture the energy as the air or other fluid which circulates through the indirect drive turbine 15 .
  • Stationary vanes will redirect the flow in to the next stage of turbine blades.
  • the indirect drive turbine 15 will produce more power.
  • the horsepower produced by the indirect drive turbine 15 could be more than the horsepower of the pump 13 or jet engine (not shown) powering the system.
  • a very important advantage of the present invention is that the gas engine 11 is not directly connected to the indirect drive turbine 15 by a drive shaft.
  • the indirect drive turbine 15 can be connected to the prop of a boat, while the gas engine 11 can be located in the front of the boat with only fluid or hydraulic lines connecting the gas engine 11 to the indirect drive turbine 15 .
  • the indirect drive turbine 15 could be connected to a rotor of a helicopter with the jet exhaust duct through the drive unit to the outside. This would constitute an open-air system, and would eliminate the need for a gear box.
  • the present invention also provides the advantage of permitting a small engine to be used for a mechanical gain from the indirect drive turbine 15 .
  • the present invention also permits the gas engine 11 to be placed where desired to best utilize the space available.
  • the present invention will increase the power output of the pump 13 by double or more, depending on the number of stages of turbine blades and stator vanes the air or other fluid passes through. Within certain limits, the more stages, the more power.
  • the present invention also includes constructing a multi-stage turbine that can be used independently or indirectly through duct work.
  • the present invention allows the unit to be powered with fluid, which will make it more practical for use in cars, trucks, and other vehicles. This will increase the horsepower output, so that a smaller motor or engine can be used. This means that much less gas will be used.
  • the turbine 15 will be made up of turbine wheels with blades that will vary in size and shape depending on the pressure, volume, and type of fluid media being used.
  • a stage is one turbine wheel and blades and one set of stator vanes. Additional stages can be added as desired.
  • the turbine is capped off at each end with an inlet duct and an outlet duct.
  • the present invention can be readily connected to a transmission or any standard drive train.
  • the engine used for the power source will not be directly physically attached to or be contiguous with a drive shaft.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

An apparatus, method and system using an indirect drive turbine to produce power by reusing spent energy by way of routing fluid flow through multiple stages of the turbine. A small engine is used for mechanical gain from the turbine. The engine is not connected to the turbine by a drive shaft.

Description

    BACKGROUND OF THE INVENTION
  • The present invention relates generally to a novel and unique indirect drive unit apparatus, and a method and system of using same.
  • More particularly, the present invention relates to to a novel and unique indirect drive unit apparatus which can be used with fluid from a gas- or electrically-driven pump or air from a jet turbine, and a method and system of using same.
  • The prior, but not necessarily relevant, art is exemplified by:
  • Wright U.S. Pat. No. 3,945,200 entitled “ROTARY ENGINE AND TURBINE ASSEMBLY”;
  • Haugen United States Patent Application Publication No. US 2006/0042247 entitled “MULTI-STAGE TURBOCHARGING SYSTEM WITH EFFICIENT BYPASS”; and
  • Rolffs et al. United States Patent Application Publication No. US 2007/00681468146 entitled “EXHAUST TREATMENT SYSTEM HAVING HYDRAULICALLY-ACTUATED AIR VALVE”.
  • It is a desideratum of the invention to avoid the animadversions of the prior art and conventional systems, and to provide a safe and effective indirect drive unit apparatus which increases the power output of a pump.
    • SUMMARY OF THE INVENTION
  • The present invention provides n indirect drive turbine apparatus, comprising: a power source; an indirect drive turbine driven by fluid flow supplied directly or indirectly by said power source; said indirect drive turbine having a drive shaft, a plurality of stages of turbine blades and stationary stator vanes to redirect said fluid flow from a first stage of said plurality of stages of turbine blades and stator vanes to a second stage of said plurality of stages of turbine blades and stator vanes; and whereby each of said plurality of stages of turbine blades and stator vanes recaptures energy as the fluid circulates through said indirect drive turbine, and each time the energy is recaptured it increases force applied to said drive shaft of said indirect drive turbine.
  • An object of the invention is to use principles used in modern jet engines by recapturing spent energy by routing it through stages of turbine blades that turn a drive shaft, and then through stationary vanes to straighten out the flow to be used again by the next stage.
  • Other objects, advantages, and features of the present invention will become apparent to those persons skilled in this particular area of technology and to other persons after having been exposed to the present patent application when read in conjunction with the accompanying patent drawings.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a schematic view of a first embodiment of the present invention.
  • FIG. 2 illustrates a perspective view, partially in cross-section, of the indirect drive turbine of FIG. 1.
  • FIG. 3 is a side elevational view of the indirect drive turbine of FIG. 2.
  • FIG. 4 is front elevational view of FIG. 3.
  • FIG. 5 is a cross-sectional view of FIG. 3.
  • FIG. 6 shows a section taken along the line 6-6 in FIG. 3.
    •  DETAILED DESCRIPTION OF THE INVENTION
  • With reference to FIG. 1, there is illustrated an indirect drive unit system and apparatus 10 which includes a gas engine 11, an exhaust pipe 12, a high volume pump 13, a storage tank 14, an indirect drive turbine 15, a turbine inlet pipe 16, a turbine shaft 17, a turbine exhaust pipe 19, and a control valve 20.
  • The exhaust pipe 12 is necessary only if a gas engine is used.
  • The arrows 21, 22, 23, 24, 25, 26 and 27 shown in FIGS. 1 and 5 indicate the direction of fluid flow.
  • The size and shape of the turbine inlet pipe 16 will vary depending in part upon the volume of fluid being used.
  • The turbine shaft 17 can be connected at a first end 18 to, for example, a transmission (not shown) or a gear box (not shown) to power any external device (not shown) which requires power.
  • The turbine shaft 17 can also be connected at a second end 31 to run, for example, a generator (not shown) or an alternator (not shown).
  • The size and shape of the turbine exhaust pipe 19 will vary with the size and shape of the turbine inlet pipe 16.
  • The turbine exhaust pipe 19 will be open to the outside air when the fluid being used is air.
  • The apparatus 10 provides a continuous system wherein the fluid is circulated from the storage tank 14 to the pump 13, and then trough the indirect drive turbine 15, and then back to the storage tank 14.
  • The control valve 20 will control the fluid flow to control or regulate the speed of the indirect drive turbine 15, with a bypass back to the storage tank 14.
  • With reference to FIGS. 2 through 6, there is shown: the inlet guide vanes and nose cone 28 which directs the fluid in to the blades and turbine wheels 29; the turbine shaft 17 which functions as a drive shaft; the fluid flow 24, 25, 26 and 27; and the turbine disk and blades 30.
  • The indirect drive turbine 15 can be used with fluid from a gas- or electrically-driven pump in a sealed system, or with air from a jet turbine or ram air from vehicle movement in a open-air system.
  • Forcing air or another fluid through a stage of turbine blades and stator vanes constitutes a first stage.
  • Each stage will recapture the energy as the air or other fluid which circulates through the indirect drive turbine 15.
  • Stationary vanes will redirect the flow in to the next stage of turbine blades.
  • Each time the energy is recaptured, this will increase the force applied to the turbine shaft 17.
  • By adding stages of turbine wheels and stator vanes, the indirect drive turbine 15 will produce more power.
  • The horsepower produced by the indirect drive turbine 15 could be more than the horsepower of the pump 13 or jet engine (not shown) powering the system.
  • A very important advantage of the present invention is that the gas engine 11 is not directly connected to the indirect drive turbine 15 by a drive shaft.
  • For example, the indirect drive turbine 15 can be connected to the prop of a boat, while the gas engine 11 can be located in the front of the boat with only fluid or hydraulic lines connecting the gas engine 11 to the indirect drive turbine 15.
  • As another example, the indirect drive turbine 15 could be connected to a rotor of a helicopter with the jet exhaust duct through the drive unit to the outside. This would constitute an open-air system, and would eliminate the need for a gear box.
  • The present invention also provides the advantage of permitting a small engine to be used for a mechanical gain from the indirect drive turbine 15.
  • The present invention also permits the gas engine 11 to be placed where desired to best utilize the space available.
  • The present invention will increase the power output of the pump 13 by double or more, depending on the number of stages of turbine blades and stator vanes the air or other fluid passes through. Within certain limits, the more stages, the more power.
  • This is accomplished by using the principles employed in modern jet engines which produce 80% more power by reusing spent energy by routing it through stages of turbine blades that turn the drive shaft 17, and then stationary vanes to straighten out the flow to be used again by the next stage.
  • The present invention also includes constructing a multi-stage turbine that can be used independently or indirectly through duct work.
  • The present invention allows the unit to be powered with fluid, which will make it more practical for use in cars, trucks, and other vehicles. This will increase the horsepower output, so that a smaller motor or engine can be used. This means that much less gas will be used.
  • The turbine 15 will be made up of turbine wheels with blades that will vary in size and shape depending on the pressure, volume, and type of fluid media being used.
  • A stage is one turbine wheel and blades and one set of stator vanes. Additional stages can be added as desired.
  • The turbine is capped off at each end with an inlet duct and an outlet duct.
  • It is important to note that the present invention can be readily connected to a transmission or any standard drive train. However, the engine used for the power source will not be directly physically attached to or be contiguous with a drive shaft.
  • There have been described hereinabove only several possible unique and novel embodiment of the present invention which can be practiced and constructed in many different configurations, materials, arrangements of components, sizes, and shapes.
  • It should be understood that many changes, modifications, variations, and other uses and applications will become apparent to those persons skilled in this particular area of technology and to others after having been exposed to the present patent specification and accompanying drawings.
  • Any and all such changes, modifications, variations and other uses and applications which do not depart from the spirit and scope of the present invention are therefore covered by and embraced within the present invention and the patent claims set forth hereinbelow.

Claims (20)

1. An indirect drive turbine apparatus, comprising:
a power source;
an indirect drive turbine driven by fluid flow supplied directly or indirectly by said power source;
said indirect drive turbine having a drive shaft, a plurality of stages of turbine blades and stationary stator vanes to redirect said fluid flow from a first stage of said plurality of stages of turbine blades and stator vanes to a second stage of said plurality of stages of turbine blades and stator vanes; and
whereby each of said plurality of stages of turbine blades and stator vanes recaptures energy as the fluid circulates through said indirect drive turbine, and each time the energy is recaptured it increases force applied to said drive shaft of said indirect drive turbine.
2. The apparatus of claim 1, wherein:
said power source includes a gas engine operatively connected to a pump which supplies said fluid flow to said indirect drive turbine.
3. The apparatus of claim 1, wherein: said fluid flow is a flow of air; and said power source comprises a jet turbine for supplying said flow of air to said indirect drive turbine.
4. The apparatus of claim 1, wherein: said fluid flow is a flow of air; and said power source comprises ram air from movement of a vehicle.
5. The apparatus of claim 1, wherein: said drive shaft is connected at a first end thereof to a transmission or a gear box, and is connected at a second end thereof to a generator or an alternator.
6. The apparatus of claim 2, wherein:
said drive shaft is connected at a first end thereof to a transmission or a gear box, and is connected at a second end thereof to a generator or an alternator.
7. The apparatus of claim 3, wherein:
said drive shaft is connected at a first end thereof to a transmission or a gear box, and is connected at a second end thereof to a generator or an alternator.
8. The apparatus of claim 4, wherein:
said drive shaft is connected at a first end thereof to a transmission or a gear box, and is connected at a second end thereof to a generator or an alternator.
9. The apparatus of claim 1, including:
an inlet conduit for conducting fluid from said power source to said indirect drive turbine;
a storage tank;
an exhaust conduit for conducting fluid from said indirect drive turbine to said storage tank;
a control valve operatively connected between said storage tank and said power source; and
whereby said control valve controls the fluid flow to control the speed of said indirect drive turbine.
10. The apparatus of claim 5, including:
an inlet conduit for conducting fluid from said power source to said indirect drive turbine;
a storage tank;
an exhaust conduit for conducting fluid from said indirect drive turbine to said storage tank;
a control valve operatively connected between said storage tank and said power source; and
whereby said control valve controls the fluid flow to control the speed of said indirect drive turbine.
11. The apparatus of claim 6, including:
an inlet conduit for conducting fluid from said power source to said indirect drive turbine;
a storage tank;
an exhaust conduit for conducting fluid from said indirect drive turbine to said storage tank;
a control valve operatively connected between said storage tank and said power source; and
whereby said control valve controls the fluid flow to control the speed of said indirect drive turbine.
12. The apparatus of claim 1, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
13. The apparatus of claim 2, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
14. The apparatus of claim 3, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
15. The apparatus of claim 4, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
16. The apparatus of claim 5, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
17. The apparatus of claim 6, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
18. The apparatus of claim 7, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
19. The apparatus of claim 8, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
20. The apparatus of claim 11, wherein:
said power source is not connected to said indirect drive turbine by a drive shaft.
US12/349,892 2009-01-07 2009-01-07 Indirect drive unit apparatus, system and method Abandoned US20100172757A1 (en)

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Cited By (1)

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Publication number Priority date Publication date Assignee Title
JP2014528544A (en) * 2011-10-04 2014-10-27 チェ, ヒョック ソンCHOI, Hyuk Sun Axial flow turbine

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US3578872A (en) * 1969-11-14 1971-05-18 Air Instr Inc Speed and torque control for surgical turbine
US5967461A (en) * 1997-07-02 1999-10-19 Mcdonnell Douglas Corp. High efficiency environmental control systems and methods
US6138649A (en) * 1997-09-22 2000-10-31 Southwest Research Institute Fast acting exhaust gas recirculation system
US20020195086A1 (en) * 1997-12-16 2002-12-26 Beck N. John Cylinder pressure based optimization control for compression ignition engines
US6470682B2 (en) * 1999-07-22 2002-10-29 The United States Of America As Represented By The Administrator Of The United States Environmental Protection Agency Low emission, diesel-cycle engine
US6301888B1 (en) * 1999-07-22 2001-10-16 The United States Of America As Represented By The Administrator Of The Environmental Protection Agency Low emission, diesel-cycle engine
US6412278B1 (en) * 2000-11-10 2002-07-02 Borgwarner, Inc. Hydraulically powered exhaust gas recirculation system
US6422219B1 (en) * 2000-11-28 2002-07-23 Detroit Diesel Corporation Electronic controlled engine exhaust treatment system to reduce NOx emissions
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