Torque-slewing diesel engine operation

Patent metadata

Field	Value
Publication number	US-11261821-B2
Application number	US-202017029505-A
Country	US
Kind code	B2
Filing date	Sep 23, 2020
Priority date	May 14, 2019
Publication date	Mar 1, 2022
Grant date	Mar 1, 2022

Abstract

An aircraft diesel engine may be operated at a minimal fuel rate. Shaft output power of the engine may be reduced by initiating combustion during the compression stroke. Combustion may be initiated during the compression stroke by advancing fuel injection, splitting fuel injection, and/or manipulating individual injection quantities. Initiating combustion during the compression stroke may slew torque generation to the compression stroke.

First claim

The invention claimed is:

1. An engine control module comprising:
one or more processors; and
memory storing instructions that, when executed by the one or more processors, cause the engine control module to receive input data regarding a 4-stroke diesel aircraft engine and to output fuel injector control signals that cause, for each of one or more cylinders of the engine:
performance of an intake stroke in which a piston moves in the cylinder between a top dead center (TDC) position and a bottom dead center (BDC) position, wherein the intake stroke is part of a cycle comprising a compression stroke, following the intake stroke, in which the piston moves between the BDC position and the TDC position, an expansion stroke, following the compression stroke, in which the piston moves between the TDC position and the BDC position, and an exhaust stroke, following the expansion stroke, in which the piston moves between the BDC position and the TDC position;
performance of the compression stroke, wherein the compression stroke comprises injection of fuel into the cylinder and combustion, by initial ignition of the fuel using heat from air compression, of at least 10% of a total mass of the fuel combusted in the cylinder during the cycle;
performance of the expansion stroke, wherein the expansion stroke comprises continued combustion of the fuel while intake and exhaust valves of the cylinder are closed; and
performance of the exhaust stroke.

2. The engine control module of claim 1 , wherein the instructions, when executed, cause the engine control module to:
receive the input data by receiving the input data while an aircraft comprising the engine is at an altitude of at least 15,000 feet above sea level; and
output the control signals by outputting the control signals while the aircraft is at the altitude of at least 15,000 feet above sea level.

3. The engine control module of claim 1 , wherein the instructions, when executed, cause the engine control module to:
receive the input data by receiving the input data while the engine is idling; and
output the control signals by outputting the control signals while the engine is idling.

4. The engine control module of claim 3 , wherein the injection of the fuel into the cylinder comprises injecting a quantity of fuel that is between f MIN and 1.10*f MIN , and wherein f MIN is a minimum quantity of fuel required to maintain stable combustion in the cylinder.

5. The engine control module of claim 3 , wherein the injection of the fuel into the cylinder comprises injecting the fuel so that a total quantity, of the fuel injected into the cylinder during the cycle, is injected in multiple injections occurring during the compression stroke.

6. The engine control module of claim 3 , wherein the engine comprises a turbocharger.

7. The engine control module of claim 1 , wherein the performance of the expansion stroke comprises performing the expansion stroke without injecting fuel into the cylinder during the expansion stroke.

8. The engine control module of claim 1 , wherein at least 15% of the total mass of the fuel combusted in the cylinder during the cycle is combusted during the compression stroke.

9. The engine control module of claim 1 , wherein at least 25% of the total mass of the fuel combusted in the cylinder during the cycle is combusted during the compression stroke.

10. An engine control module comprising:
one or more processors; and
memory storing instructions that, when executed by the one or more processors, cause the engine control module to receive input data regarding a 4-stroke diesel aircraft engine and to output fuel injector control signals that cause, for each of one or more cylinders of the engine:
operation of the engine at a first shaft output power, wherein, for each of one or more cylinders of the engine:
a cycle comprises an intake stroke in which a piston moves in the cylinder between a top dead center (TDC) position and a bottom dead center (BDC) position, a compression stroke, following the intake stroke, in which the piston moves between the BDC position and the TDC position and in which fuel is initially ignited using heat from air compression, an expansion stroke, following the compression stroke, in which the piston moves between the TDC position and the BDC position, and an exhaust stroke, following the expansion stroke, in which the piston moves between the BDC position and the TDC position, and
a first percentage of a first total mass of the fuel combusted, during each cycle at the first shaft output power, is combusted during the compression stroke; and

operation of the engine at a second shaft output power, wherein, for each of the one or more cylinders of the engine:
a second percentage of a second total mass of fuel combusted, during each cycle at the second shaft output power, is combusted during the compression stroke,
the second shaft output power is less than the first shaft output power, and
the second percentage is higher than the first percentage.

11. The engine control module of claim 10 , wherein the second percentage is at least 20%.

12. The engine control module of claim 10 , wherein the second percentage is at least 30%.

13. The engine control module of claim 10 , wherein the operation of the engine at the second shaft output power comprises operating the engine while an aircraft comprising the engine is at an altitude of at least 15,000 feet above sea level.

14. The engine control module of claim 10 , wherein the operation of the engine at the second shaft output power comprises idling the engine.

15. The engine control module of claim 14 , wherein the operation of the engine at the second shaft output power comprises operating the engine while an aircraft comprising the engine is at an altitude of at least 15,000 feet above sea level.

16. An engine control module comprising:
one or more processors; and
memory storing instructions that, when executed by the one or more processors, cause the engine control module to receive input data regarding a 4-stroke diesel aircraft engine and to output fuel injector control signals that cause, for each of one or more cylinders of the engine:
combustion, in the cylinder during a compression stroke, of a first portion of a total mass of fuel combusted during a cycle comprising the compression stroke, wherein the compression stroke comprises initial ignition of the fuel using heat from air compression; and
combustion, in the cylinder during an expansion stroke immediately following the compression stroke, of a second portion of the total mass of the fuel combusted during the cycle, wherein
the first portion is at least 10% of a sum of the first and second portions.

17. The engine control module of claim 16 , wherein the first portion is at least 20% of the sum of the first and second portions.

18. The engine control module of claim 16 , wherein the first portion is at least 30% of the sum of the first and second portions.

19. The engine control module of claim 16 , wherein, for each of the one or more cylinders, no fuel is injected into the cylinder during the expansion stroke.

20. The engine control module of claim 16 , wherein the instructions, when executed, cause the engine control module to:
receive the input data by receiving the input data while the engine is idling; and
output the control signals by outputting the control signals while the engine is idling.

Assignees

• Science Appl Int Corp
• Government Of The United States As Represented By The Secretary Of The Army
• Science Application Int Corporation
• Us Gov Sec Army

Inventors

• Meininger Rik Denis
• Acker Bernard

Classifications

• F02D41/402 Primary

  Multiple injections · CPC title

• F02D41/08

  for idling (F02D41/06, F02D41/16 take precedence) · CPC title

• B64D27/08

  within, or attached to, fuselages · CPC title

• F02D41/401

  Controlling injection timing (F02D41/402 takes precedence) · CPC title

• F02D2200/501

  Vehicle speed · CPC title