CN114852354A - Fuel oil system - Google Patents
Fuel oil system Download PDFInfo
- Publication number
- CN114852354A CN114852354A CN202210415581.XA CN202210415581A CN114852354A CN 114852354 A CN114852354 A CN 114852354A CN 202210415581 A CN202210415581 A CN 202210415581A CN 114852354 A CN114852354 A CN 114852354A
- Authority
- CN
- China
- Prior art keywords
- fuel
- oil
- temperature
- pump
- fuel oil
- 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.)
- Pending
Links
- 239000000295 fuel oil Substances 0.000 title claims abstract description 63
- 239000000446 fuel Substances 0.000 claims abstract description 156
- 239000003921 oil Substances 0.000 claims abstract description 29
- 239000010687 lubricating oil Substances 0.000 claims abstract description 11
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 239000000203 mixture Substances 0.000 claims abstract description 3
- 230000000630 rising effect Effects 0.000 claims abstract description 3
- 238000011045 prefiltration Methods 0.000 claims description 2
- 230000001351 cycling effect Effects 0.000 claims 1
- 238000010304 firing Methods 0.000 abstract 1
- 239000000654 additive Substances 0.000 description 4
- 239000010705 motor oil Substances 0.000 description 4
- 125000004122 cyclic group Chemical group 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000001914 filtration Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 230000000996 additive effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 231100001261 hazardous Toxicity 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The application provides a fuel oil system, fuel oil system includes that aircraft tank, fuel booster pump, fuel oil radiator, fuel filter, fuel pump regulator and fuel oil distributor, the aircraft tank provides fuel oil system's fuel oil and comes the oil, fuel oil system is still including the fuel oil return flow path of connecting the terminal and fuel pump regulator gear pump rear side of fuel booster pump, fuel oil return flow path is from the gear pump rear side oil return of fuel pump regulator to fuel oil booster pump rear end, before engine fuel oil radiator, joins the temperature that promotes the fuel from the high temperature oil return of fuel pump regulator and the cold oil that comes from the fuel oil booster pump, and simultaneously, the fuel after the mixture gets into fuel oil radiator, gets into the fuel oil after further heat transfer rising temperature with the lubricating oil and strains. The utility model provides a fuel oil system has promoted anti-icing ability, can avoid circulation heating to make under the high entry fuel temperature fuel oil temperature surpass the temperature resistance ability of fuel pump regulator after firing the lubricating oil radiator simultaneously.
Description
Technical Field
The application relates to the technical field of aircraft engines, in particular to a fuel system.
Background
The low temperature of the airplane flying at high altitude (for example, the temperature of the airplane can reach-56 ℃ in the high altitude of 11000 m) can have harmful influence on a fuel system and parts, and the low temperature enables water in the fuel to be analyzed and even frozen, so that a valve, a pump, a filter and a filter screen are blocked, the fuel system fails and normal fuel supply to an engine cannot be realized, and the hazardous influence is caused on the flying safety.
In order to avoid flight accidents caused by the fact that oil supply of an engine is interrupted or completely stopped due to icing of an oil supply system when an airplane flies at high altitude for a long time, the engine development requires that an engine fuel system stably works at an inlet temperature of more than 40 ℃ below zero.
The specification for icing of fuel according to aeroengine airworthiness regulations (CCAR-33R2) item 33.67 b (4) (ii) states: the fuel system continues to operate throughout its flow and pressure range with the addition of 0.2 ml of free water per liter of initial saturated fuel containing water at 27 c and cooling to the most dangerous icing conditions likely to be encountered in operation. However, this requirement can be met by verifying the effectiveness of certain approved fuel anti-icing additives; or the fuel system is provided with a fuel heater to keep the fuel temperature at the fuel filter or fuel inlet above 0 ℃ under the most dangerous icing condition.
As shown in the schematic diagram of the engine fuel system of fig. 1, in the engine fuel system, because the fuel booster pump is a centrifugal pump, icing has little influence on the fuel booster pump, and the damage to the fuel filter of a small channel is the greatest. Typically, the engine oil radiator is placed before the fuel filter, and the heat of the engine oil is used to warm the fuel, similar to the effect of a heater. In addition, anti-icing additives and other improvement measures can be added into the fuel oil, so that the problem of serious icing of an aircraft fuel oil system is solved. However, the heat dissipation capacity of the engine oil is limited, and when the temperature of the engine inlet fuel is low, such as below-30 ℃, the temperature of the fuel passing through the engine oil radiator cannot be raised to zero. There is still a risk of icing; due to the fact that the amount of fuel oil is large, more additives need to be carried by adopting the additive scheme, and flying weight is increased.
Disclosure of Invention
It is an object of the present application to provide a fuel system to address or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: the utility model provides a fuel oil system, fuel oil system includes that aircraft tank, fuel booster pump, fuel oil radiator, fuel oil strain, fuel pump regulator and fuel oil distributor, aircraft tank provides fuel oil system's fuel oil and comes the oil, fuel oil system is still including the fuel oil return flow path of connecting the terminal and fuel pump regulator gear pump rear side of fuel oil booster pump, fuel oil return flow path returns oil to fuel oil booster pump rear end from the gear pump rear side of fuel pump regulator, before the engine fires the fuel oil radiator, joins the temperature that promotes the fuel oil with the cold oil that comes from the fuel oil booster pump from the high temperature oil return of fuel pump regulator, and simultaneously, the fuel oil after the mixture gets into the fuel oil radiator, gets into the fuel oil after further heat transfer rising the temperature with the lubricating oil and strains.
Furthermore, a control valve is arranged on the fuel oil return path, and an opening signal of the control valve is controlled by an engine inlet fuel oil temperature parameter or a fuel oil radiator rear temperature.
Further, when the temperature of the fuel at the inlet of the engine is higher than 0 ℃, the control valve is closed to prevent the temperature of the fuel which is higher than the temperature of the inlet fuel from exceeding the temperature resistance of the fuel pump regulator after the fuel passes through the fuel radiator due to cyclic heating.
Further, the fuel flow of the fuel return flow path is obtained through analysis and calculation of typical states in an envelope.
Further, the temperature yield of the fuel system before fuel filtration is as follows:
in the formula: m1 and T1 are respectively the fuel flow and the fuel temperature of the outlet of the fuel booster pump;
m2 and T2 are respectively the fuel flow and the temperature of the oil return flow path;
q1 is the heat quantity transferred to the fuel by the lubricating oil corresponding to the fuel flow of the fuel booster pump outlet;
q2 is the heat transferred to the fuel by the oil corresponding to the fuel flow and the return flow of the fuel booster pump outlet.
The fuel system has the advantages that the anti-icing capability is improved on the basis of the original heating by using the lubricating oil of the engine by adding the fuel loop from the fuel pump regulator to the fuel booster pump and mixing the hot oil with the cold oil after the booster pump; meanwhile, when the temperature of the fuel at the inlet of the engine is higher, the control valve is closed, and the situation that the temperature of the fuel at the high inlet fuel temperature exceeds the temperature resistance of the fuel pump regulator after the fuel passes through the fuel radiator due to cyclic heating is avoided.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic flow diagram of a prior art fuel system.
FIG. 2 is a schematic flow diagram of a fuel system of the present application.
FIG. 3 is a thermal power curve of an exemplary embodiment of a fuel-fired radiator.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
As shown in fig. 2, the present application provides a fuel system for improving fuel heat dissipation, which is based on an existing fuel loop, and adds a fuel return flow path in a fuel flow path, wherein the fuel return flow path connects a terminal of a fuel booster pump and a fuel pump regulator, the fuel return flow path returns from a gear pump of the fuel pump regulator to a rear end of the fuel booster pump, and before an engine fuel radiator, high-temperature return oil from the fuel pump regulator is merged with cold oil from the fuel booster pump to raise the temperature of the fuel, and meanwhile, the mixed fuel enters the fuel radiator, and enters a fuel filter after further exchanging heat with the lubricant to raise the temperature.
In the fuel system of the application, a control valve is arranged on a fuel return circuit, and an opening signal of the control valve is controlled by an engine inlet fuel temperature parameter or the temperature behind a fuel oil radiator.
In the fuel system of the present application, the fuel flow rate of the hot return flow path may be obtained by an analysis calculation of typical conditions within the envelope.
In this application, when engine entry fuel temperature is greater than 0 degree, control flap closes, avoids circulation heating to make under the high entry fuel temperature the temperature behind the fuel oil radiator exceed the temperature-resistant ability of fuel pump regulator.
In addition, this application still provides the method for confirming the pre-filtration temperature income of fuel of above-mentioned fuel system, includes:
determining that the fuel flow m1 'and the fuel temperature T1' of the inlet of the fuel oil radiator satisfy the following conditions when the control valve is closed:
m1'＝m1，T1'＝T1 (1)
in the formula, m1 and T1 are respectively the fuel flow and the fuel temperature of the outlet of the fuel booster pump;
m2 and T2 are respectively the fuel flow and the temperature of the oil return flow path;
m3 and T3 are respectively the fuel flow and the temperature of the fuel radiator outlet/fuel filter inlet;
according to the thermodynamic curve of the fuel oil radiator, determining the heat transferred to the fuel oil by the fuel oil corresponding to the fuel oil flow m 1: q1 ═ f (m1) · [ Toil-T1] (2)
Where f (m1) is the ordinate value for the thermodynamic curve and Toil is the oil temperature, in terms of heat exchanger heat exchange equilibrium: m 1. Cp1 (T3-T1) ═ Q1 (3)
It can be seen that when the control valve is closed without hot oil return, the temperature T3 at the outlet of the oil-fired radiator is:
T3＝Q1/(m1·Cp1)+T1 (4)
when the temperature of the incoming oil is lower and the control valve is opened:
m1'＝m1+m2 (5)
T1'＝(m1·Cp1·T1+m2·Cp2·T2)/(m1·Cp1+m2·Cp2) (6)
according to the thermodynamic curve of the fuel oil radiator, the heat quantity transferred to the fuel oil by the fuel oil corresponding to the fuel oil flow (m1+ m2) is as follows: q2 ═ f (m1+ m2) · [ Toil-T1' ] (7)
Wherein f (m1+ m2) is the ordinate value corresponding to the thermodynamic curve, according to the heat exchanger heat exchange equilibrium: m1 '. Cp1' · (T3 '-T1'). Q2 (8)
Therefore, when the control valve opens the hot oil return,
T3'＝Q2/(m1'·Cp1')+T1' (9)
T3'＝Q2/[(m1+m2)·Cp1']+(m1·Cp1·T1+m2·Cp2·T2)/(m1·Cp1+m2·Cp2) (10)
according to the results (4) and (10), the temperature gain of the fuel before filtering is as follows:
ΔT＝T3'-T3 (11)
because the temperature has little influence on the heat capacity, the temperature-specific heat capacity can be obtained after simplification:
the fuel system has the advantages that the anti-icing capability is improved on the basis of the original heating by using the lubricating oil of the engine by adding the fuel loop from the fuel pump regulator to the fuel booster pump and mixing the hot oil with the cold oil after the booster pump; meanwhile, when the temperature of the fuel at the inlet of the engine is higher, the control valve is closed, and the situation that the temperature of the fuel at the high inlet fuel temperature exceeds the temperature resistance of the fuel pump regulator after the fuel passes through the fuel radiator due to cyclic heating is avoided.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. The utility model provides a fuel oil system, fuel oil system includes aircraft tank, fuel booster pump, fires the lubricating oil radiator, the fuel is strained, fuel pump regulator and fuel oil distributor, aircraft tank provides fuel oil system's fuel oil and comes the oil, its characterized in that, fuel oil system is still including the fuel oil return flow path who connects the terminal and fuel pump regulator gear pump rear side of fuel booster pump, fuel oil return flow path returns oil to fuel pump rear end from the gear pump rear side of fuel pump regulator, before the engine fires the lubricating oil radiator, converges with the cold oil that comes from the fuel pump booster pump from the high temperature oil return of fuel pump regulator and promotes the temperature of fuel oil, and simultaneously, the fuel after the mixture gets into fires the lubricating oil radiator, gets into the fuel oil after rising the temperature with the lubricating oil further heat transfer and strains.
2. The fuel system as recited in claim 1, wherein a control valve is disposed on said fuel circuit, and wherein an opening signal of said control valve is controlled by an engine inlet fuel temperature parameter or a post-radiator temperature of the fuel.
3. The fuel system as recited in claim 2, wherein said control valve is closed when the engine inlet fuel temperature is greater than 0 degrees to avoid cycling heating such that fuel above the inlet fuel temperature passes through the fuel radiator to a temperature exceeding the temperature capability of the fuel pump regulator.
4. The fuel system as recited in claim 1, wherein said fuel flow rate of said fuel return flow path is calculated by an analysis of typical conditions within the envelope.
5. The fuel system as recited in claim 1, wherein the pre-filter temperature gain for fuel is:
in the formula: m1 and T1 are respectively the fuel flow and the fuel temperature of the outlet of the fuel booster pump;
m2 and T2 are respectively the fuel flow and the temperature of the oil return flow path;
q1 is the heat quantity transferred to the fuel by the lubricating oil corresponding to the fuel flow of the fuel booster pump outlet;
q2 is the heat transferred to the fuel by the oil corresponding to the fuel flow and the return flow of the fuel booster pump outlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210415581.XA CN114852354A (en) | 2022-04-18 | 2022-04-18 | Fuel oil system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210415581.XA CN114852354A (en) | 2022-04-18 | 2022-04-18 | Fuel oil system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114852354A true CN114852354A (en) | 2022-08-05 |
Family
ID=82631523
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210415581.XA Pending CN114852354A (en) | 2022-04-18 | 2022-04-18 | Fuel oil system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114852354A (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6584777B1 (en) * | 1999-06-16 | 2003-07-01 | Rolls-Royce Plc | Apparatus for and method of filtering a fluid |
| JP2004027874A (en) * | 2002-06-21 | 2004-01-29 | Mitsubishi Heavy Ind Ltd | Gas turbine icing preventing method and icing preventing system |
| RU2435709C1 (en) * | 2010-05-31 | 2011-12-10 | Закрытое акционерное общество "Гражданские самолеты Сухого" | Method of fuel temperature regulation in airplane fuel system |
| US20130186100A1 (en) * | 2012-01-20 | 2013-07-25 | Hamilton Sundstrand Corporation | Small engine cooled cooling air system |
| CN203572657U (en) * | 2013-10-30 | 2014-04-30 | 中国南方航空工业(集团)有限公司 | Parameter measuring device of internal fuel oil pipeline system of aero-engine |
| CN104395595A (en) * | 2012-07-05 | 2015-03-04 | 联合工艺公司 | Fuel preheating using electric pump |
| US20160297538A1 (en) * | 2013-12-03 | 2016-10-13 | Eads Construcciones Aeronauticas | Aircraft fuel system with heating of stored fuel |
| US10752374B1 (en) * | 2017-03-15 | 2020-08-25 | Northrop Grumman Systems Corporation | Active fuel thermal conditioning for aircraft |
| CN211598881U (en) * | 2019-11-13 | 2020-09-29 | 潍柴动力股份有限公司 | Fuel system for diesel engine, diesel engine with fuel system and vehicle |
| US20210229827A1 (en) * | 2015-10-08 | 2021-07-29 | Government Of The United States, As Represented By The Secretary Of The Air Force | Thermal management system and method of using same |
| CN114151149A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Gas turbine engine fuel oil heat management and anti-icing integrated control system |
-
2022
- 2022-04-18 CN CN202210415581.XA patent/CN114852354A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6584777B1 (en) * | 1999-06-16 | 2003-07-01 | Rolls-Royce Plc | Apparatus for and method of filtering a fluid |
| JP2004027874A (en) * | 2002-06-21 | 2004-01-29 | Mitsubishi Heavy Ind Ltd | Gas turbine icing preventing method and icing preventing system |
| RU2435709C1 (en) * | 2010-05-31 | 2011-12-10 | Закрытое акционерное общество "Гражданские самолеты Сухого" | Method of fuel temperature regulation in airplane fuel system |
| US20130186100A1 (en) * | 2012-01-20 | 2013-07-25 | Hamilton Sundstrand Corporation | Small engine cooled cooling air system |
| CN104395595A (en) * | 2012-07-05 | 2015-03-04 | 联合工艺公司 | Fuel preheating using electric pump |
| CN203572657U (en) * | 2013-10-30 | 2014-04-30 | 中国南方航空工业(集团)有限公司 | Parameter measuring device of internal fuel oil pipeline system of aero-engine |
| US20160297538A1 (en) * | 2013-12-03 | 2016-10-13 | Eads Construcciones Aeronauticas | Aircraft fuel system with heating of stored fuel |
| US20210229827A1 (en) * | 2015-10-08 | 2021-07-29 | Government Of The United States, As Represented By The Secretary Of The Air Force | Thermal management system and method of using same |
| US10752374B1 (en) * | 2017-03-15 | 2020-08-25 | Northrop Grumman Systems Corporation | Active fuel thermal conditioning for aircraft |
| CN211598881U (en) * | 2019-11-13 | 2020-09-29 | 潍柴动力股份有限公司 | Fuel system for diesel engine, diesel engine with fuel system and vehicle |
| CN114151149A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Gas turbine engine fuel oil heat management and anti-icing integrated control system |
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