GB2095756A - Balancing the heat flow between components associated with a gas turbine engine - Google Patents
Balancing the heat flow between components associated with a gas turbine engine Download PDFInfo
- Publication number
- GB2095756A GB2095756A GB8206536A GB8206536A GB2095756A GB 2095756 A GB2095756 A GB 2095756A GB 8206536 A GB8206536 A GB 8206536A GB 8206536 A GB8206536 A GB 8206536A GB 2095756 A GB2095756 A GB 2095756A
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- GB
- United Kingdom
- Prior art keywords
- fuel
- heat
- engine
- electrical generator
- heat exchanger
- 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
Links
- 239000000446 fuel Substances 0.000 claims abstract description 221
- 238000001816 cooling Methods 0.000 claims abstract description 29
- 238000004891 communication Methods 0.000 claims abstract description 25
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 17
- 239000012809 cooling fluid Substances 0.000 claims description 47
- 239000007789 gas Substances 0.000 claims description 43
- 239000012530 fluid Substances 0.000 claims description 19
- 239000010705 motor oil Substances 0.000 claims description 14
- 238000002485 combustion reaction Methods 0.000 claims description 13
- 230000015572 biosynthetic process Effects 0.000 claims description 7
- 230000003134 recirculating effect Effects 0.000 claims description 6
- 230000001052 transient effect Effects 0.000 claims description 6
- 230000009467 reduction Effects 0.000 claims description 5
- 239000003921 oil Substances 0.000 claims description 4
- 239000002918 waste heat Substances 0.000 claims description 3
- 239000012188 paraffin wax Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 claims 6
- 230000000694 effects Effects 0.000 claims 1
- 238000007710 freezing Methods 0.000 claims 1
- 230000008014 freezing Effects 0.000 claims 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims 1
- 230000006835 compression Effects 0.000 description 8
- 238000007906 compression Methods 0.000 description 8
- 238000010438 heat treatment Methods 0.000 description 7
- 239000010687 lubricating oil Substances 0.000 description 6
- 239000002828 fuel tank Substances 0.000 description 4
- 230000007423 decrease Effects 0.000 description 3
- 230000002401 inhibitory effect Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
-
- 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
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Heat transfer systems for maintaining a thermal balance between a gas turbine engine and heat generating accessory components of the engine are disclosed. In the embodiment illustrated, heat is removed from the cooling system 48 of an electrical generator 46 and is transferred to the fuel supply system 32 of the engine. In one detailed embodiment, the cooling system 48 is in direct heat transfer communication with the downstream portion 62 of the fuel supply system through a heat exchanger 76 and in indirect heat transfer communication with the upstream portion 60 of the fuel supply system through the fuel recirculation system 42. <IMAGE>
Description
SPECIFICATION
Balancing the heat flow between components associated with a gas turbine engine
Technical field
This invention relates to axial flow gas turbine engines and particularly to the maintenance of a thermal balance between components which require cooling and components which require heating.
The components were developed in the gas turbine engine industry for matching the inverse heating and cooling requirements of the engine fuel control and electrical generator, but are more widely applicable to other components with similar heat load requirements.
Background art
Axial flow gas turbine engines are typically formed of a compression section, a combustion section and a turbine section. Working medium gases are drawn into the compression section where they pass through several stages of compression causing the temperature and the pressure of the gases to rise. The gases are mixed with the fuel in the combustion section and burned to form hot pressureized gases. The gases are a source of energy to the engine. These gases are expanded through the turbine section to produce work. Both the compression section and the turbine section contain moving components, such as bearings, Lubricating oil is flowed to these components to both lubricate the components and to remove heat from the components.The heat gained by the lubricating oil is rejected to the fuel system as fuel is flowed from a source of fuel through a fuel control to the combustion section of the engine.
In fixed wing aircraft, such as those for which the present concepts were developed, the engine is mounted in a housing attached to a wing of the aircraft. The housing both supports and positions the engine with respect to the aircraft. Such aircraft fly at high altitudes for long periods of time at temperatures as low as 650F below zero (--650F). This low temperature cools the fuel in the fuel supply tanks to a low temperature. To block the formation of ice in critical components in the fuel supply system such as the fuel control, hot working medium gases are diverted from the working medium flow path of the compression section through a heater to heat the fuel. This heater is typically located in the nacelle in a compartment such as the core compartment.
Another piece of auxiliary equipment disposed in the nacelle compartment is an electrical generator for supplying aircraft electric power.
The production of electric power is accompanied by the production of heat which must be removed to preserve the operating life of the electrical generator. A construction for removing the heat is shown in U.S. Patent No. 4,151,710 entitled "Lubrication Cooling System for Aircraft Engine
Accessory" issued to Griffin et al. In Griffin, the heat is removed by lubricating oil passing through the generator. The heat is rejected to cooling air through a primary heat exchanger located in a working medium flow path of the engine and to the fuel through a secondary heat exchanger in communication with fuel being flowed to the combustion chambers.
Another approach to cooling the electrical generator is described in a copending U.S. patent application, Seriag Number , assigned to the assignee of this invention. Heat is rejected primarily to fuel through a heat exchanger in communication with fuel being flowed to the combustion chambers and secondarily to air ducted from the working medium flow path through an on/off heat exchanger remote from the flow path which is located in a nacelle compartment. Using fuel as the primary coolant results in the recovery of energy from the electrical generator by the engine. In addition, using fuel as the primary coolant reduces the size of the cooling air heat exchanger and enables installation of the heat exchanger in a compartment remote from the airstream to minimize the intrusion of the heat exchanger into the airstream.
Disclosure of the invention
According to the present invention, a thermal balance is maintained between a gas turbine engine and accessory components of the engine by transferring heat from an electrical generator driven by the engine to a fuel control controlling the flow of fuel to the engine for the purposes of inhibiting the formation of ice in the fuel control and, at the same time, cooling the electrical generator.
In accordance with one specific embodiment of the present invention, heat transferred to the cooling system of the electrical generator from the fuel system downstream of the fuel control during a transient imbalance in the fuel system resulting from a sudden decrease in engine power is transferred back to the fuel system upstream of the fuel control to cool the cooling system and to heat the fuel control.
Thcs invention is predicated on the recognition that such a cooling system may be improved by recovering additional energy in the form of heat from the electrical generator rather than by rejecting such heat to cooling air bypassed from the working medium flow path. The additional energy recovered in the form of heat is used to replace heat for the fuel control previously obtained from the hot working medium gases bypassed from the primary flow path for heating.
A primary feature of the present invention is an electrical generator which produces waste heat and thus is capable of acting as a source of heat.
Another feature of the present invention is a fuel control which requires heating at low temperatures. A heat exchanger is in fluid communication with cooling fluid flowed through the electrical generator and the fuel flowed through the fuel control. In one specific embodiment the heat exchanger is in fluid communication with a conduit for recirculating pressurized fuel from an outlet in the fuel control through a hydraulic vane controller to an inlet in the fuel control. In another embodiment, a first heat exchanger is disposed in the fuel line downstream of the fuel control for transferring heat from the engine oil to the engine fuel. A second heat exchanger is disposed in the fuel line downstream of the first heat exchanger for transferring heat from the cooling fluid to the engine fuel.A fourth heat exchanger for transferring heat from the cooling fluid to low temperature working medium gases is in fluid communication with the electrical generator.
A primary advantage of the present invention is the gain in engine efficiency which results from inhibiting the formation of ice in the fuel control with waste heat from the electrical generator rather than by transferring heat from the working medium flow path of the engine to perform the inhibiting function. Another advantage is the gain in engine efficiency which results from using the fuel flowed through the fuel control as a heat sink during flight idle operation rather than by removing an equivalent amount of heat from the generator cooling fluid in a heat exchanger cooled by fan air.
In one specific embodiment, an advantage is the efficiency which results from rejecting heat to the fuel entering the fuel control during transient conditions following a sudden reduction in power when, because of a temporary temperature imbalance, the fuel downstream of the fuel control rejects heat to the cooling fluid through a heat exchanger between the fuel and the cooling fluid.
The foregoing, and other objects, features and advantages of the present invention will become more apparent in the light of the following detailed description of the preferred embodiment thereof as shown in the accompanying drawing.
Brief description of the drawings
Fig. 1 is a partial perspective view of an axial flow gas turbine engine of the turbofan type mounted in an aircraft nacelle with a portion of the fan compartment and the core compartment broken away to show portions of the engine and accessory equipment.
Fig. 2 is a diagrammatic illustration of the primary flow path, the secondary flow path of the gas turbine engine and a portion of the accessory equipment disposed in the nacelle core compartment about the gas turbine engine.
Fig. 3 is a schematic diagram of a portion of the fuel supply system, a fuel recirculation system and a cooling system for the electrical generator.
Best mode for carrying out the invention
A gas turbine engine 10 of the axial flow turbo fan type is shown in Fig. 1. A nacelle 12 circumscribes the engine. The nacelle is adapted to both support and position the engine from a support structure such as an aircraft wing. The nacelle includes compartments for housing auxiliary equipment such as nacelle fan compartment 14 and a nacelle core compartment 16.
As shown diagrammatically in Fig. 2, the core compartment 1 6 is spaced radially inwardly of the fan compartment 14 leaving a fan bypass duct 18 therebetween. A secondary flow path 20 for working medium gases extends through the bypass duct. A primary flow path 22 for working medium gases extends rearwardly through the engine which is formed of a fan section 24, a compressor section 26, a combustion section 28 and a turbine section 30. A fuel supply system 32 is in fluid communication with the combustion section.
The fan section and the compressor section together are commonly referred to as the compression section. The compression section and the turbine section include rotor components 34 and stator components 36. The stator components include variable stator vanes 38 which extend across the primary flow path 22 for working medium gases. A hydraulic vane controller 40 for positioning the vanes is linked to the vanes. A fuel recirculation system 42 for providing hydraulic power is in fluid communication with the hydraulic vane controller. An engine oil system 44 is provided for lubricating rotating components such as bearings which support the rotor components.
A component which produces excess heat, such as an electrical generator 46 for supplying electric power to the aircraft at a constant frequency, is also housed in the core compartment 16. The electrical generator is driven by the gas turbine engine. A cooling system 48 for the electrical generator is in fluid communication with the generator.
Fig. 3 shows in greater detail the cooling system 48, the fuel recirculation system 42 and the fuel supply system 32. The fuel supply system includes a fuel tank 50 typically disposed in the wing of the aircraft, a main fuel pump 52 and fuel control 54, and a means for injecting fuel into the combustion chamber of the engine such as a fuel nozzle 56. A fuel line 58 for ducting fuel extends from-the tanks through the main fuel pump and fuel control to the fuel nozzle.
The fuel supply system 32 has an upstream portion 60 and a downstream portion 62. The upstream portion extends between the fuel tank 50 and the fuel control 54. The downstream portion extends between the fuel nozzle 56 and the fuel control. The fuel control is adapted by an outlet 64 to discharge fuel into the downstream portion of the fuel supply system and by an inlet 66 to receive fuel from the upstream portion of the fuel supply system. The upstream portion includes a filter 68 and a means for heating the engine fuel such as the heat exchanger 70. The heat exchanger is in fluid communication with a source of heat such as hot working medium gases from the primary flow path. For example, these gases might be drawn from a rear stage of the compressor section.A valve 72 for controlling the
flow of hot gases through the heat exchanger is
responsive to the temperature of the fuel entering
the fuel control. The downstream portion 62 of
the fuel system includes a means, such as a first
heat exchanger 74 for transferring heat from the
engine oil to the fuel. The downstream portion
also includes a means, such as a second heat
exchanger 76, for transferring heat between the
fuel in the fuel line and cooling fluid in the cooling
system 48 for the electrical generator.
The fuel recirculation system 42 extends
between the downstream portion 62 of the fuel
system and the upstream portion 60. The fuel
recirculation system includes a means, such as a
third heat exchanger 78, for transferring heat from the cooling fluid in the cooling system 48 to
the fuel in the fuel recirculation system. The fuel
recirculation system includes a conduit 80. This
conduit is in fluid communication with the outlet
64 of the fuel control, the hydraulic vane
controller 40, the third heat exchanger 78 and the
inlet 66 of the fuel control. As will be realized, the
conduit may be in fluid communication with the
inlet of the fuel control through the upstream
portion of the fuel line either upstream or
downstream of the filter 68 or downstream of the
pump 52.
The cooling system 48 for the electrical generator 46 includes a means, such as a fourth heat exchanger 82, for transferring heat from the cooling fluid to cooling air. A conduit 84 extends between the fan duct 1 8 and the fourth exchanger to place the fourth heat exchanger in fluid communication with a source of cooling air.
The cooling air is discharged from the heat exchanger and exhausted into a nacelle compartment such as the nacelle fan compartment 14 or the nacelle core compartment
1 6. A valve 86 for regulating the fan air flow through the conduit 84 is responsive to the temperature of the cooling fluid in the cooling
system 48 at the point of discharge from the electrical generator. A means 88 for circulating the cooling fluid in the cooling system includes a pump (not shown) and a conduit 90. As will be realized, the pump might be an integral portion of the electrical generator. The means is used to place the cooling fluid in fluid and heat transfer communication with the electrical generator, the fourth heat exchanger, the third heat exchanger 78 and the second heat exchanger 76.The means 88 for circulating the cooling fluid includes a bypass conduit 92 which connects the inlet and the outlet of the third heat exchanger to prevent the transfer of an excessive amount of heat to the fuel. A valve 94 responsive to the temperature of the fuel in the fuel recirculation system 42 is used to regulate the flow of cooling fluid through the third heat exchanger. A second bypass conduit 96 connects the inlet and discharge ports of the second heat exchanger to prevent the loss of heat from the cooling fluid during low temperature start-up of the engine. A valve 98 responsive to the temperature of the cooling fluid and the cooling system regulates the flow of cooling fluid through the bypass conduit around the second heat exchanger.
During operation of the gas turbine engine,
working medium gasses in the form of air are drawn
into the gas turbine engine and compressed in the
compressor section 26 causing the temperature
and the pressure of the working medium gases to
increase. The gases are flowed to the combustion section. Fuel from the fuel tank 50 is injected by
the fuel nozzle 56 into the coribustion section 28.
The fuel and gases are mixed and burned to increase the temperature ofthe working medium gases. The gases are expanded through the turbine section 30 to power the aircraft to which the engine is attached.
Moving components of the engine are lubricated by engine oil flowed through the engine oil system 44 to the components. The oil reduces but does not eliminate friction between the parts.
Heat generated by this friction is transferred to the engine oil and is carried by the oil to the first
heat exchanger 74. The heat is transferred from the engine oil to fuel flowed through the fuel supply system 32 to the fuel nozzles 56. Heat is also produced by the electrical generator 46. This heat results primarily from resistance heating of the generator elements during the production of aircraft power and secondarily from mechanical friction and viscous friction associated with operation of the electrical generator and pumping of the cooling fluid. The heat is transferred to the cooling fluid which is flowed through the cooling system 48. As with the engine bearings, the cooling fluid is preferably the lubricating oil.After the cooling fluid is flowed through the electrical generator the heat from the cooling fluid is rejected under most operating conditions to both the combustion fuel in the downstream portion 62 of the fuel supply via the second heat exchanger 76 and to the pressurized fuel in the fuel recirculation system 42 via the third heat exchanger 78. The pressuruzed fuel is flowed to the fuel control 54. Heat is transferred from the fuel to the fuel control.
At low power operation the flow of combustion fuel passing through the first and second heat exchangers 74, 76 in the downstream fuel line is much reduced as compared with high power operation. The amount of heat transferred from the hot lubricating oil of the engine through the first heat exchanger to the combustion fuel coupled with the low fuel flow at low power greatly raises the temperature of the fuel. The higher temperature of the fuel diminishes at low power the ability of the second heat exchanger to remove heat from the cooling fluid passing through the electrical generator 46. By rejecting heat from the cooling fluid via the third heat exchanger 78 to fuel in the recirculation system 42, the need for using the fourth heat exchanger 82 is reduced and, in most cases, is completely eliminated. This is important because the fourth heat exchanger is used to transfer heat from the cooling fluid to working medium gases flowed from the compression section of the engine. As will be realized the loss of these gases, for example, from the secondary flow path 20,
decreases the efficiency of the engine.
Use of the third heat exchanger 78 is also important at high altitude, low power operation.
At high altitude operation, the fuel flowing from the fuel tank 50 may be at temperatures as low as sixty-five degrees Fahrenheit below zero (-650F; -530C). The presence of moisture in the fuel may cause ice to form in a fuel. The transfer of heat from the cooling fluid in the cooling system to the recirculated fuel blocks the formation of ice in the fuel control at most low power operating conditions. The recirculated fuel also carries heat from the third heat exchanger to fuel entering the filter. This heat warms the fuel to a temperature which blocks the accretion of wax-like paraffin on the filter and accordingly avoids the deterioration in filter performance associated with such a build-up.Thus, use of the third heat exchanger avoids at low power (reduces at high power) the need to use hot working medium gases diverted from the primary flow path to the heat exchanger 70 for heating the fuel. In summary, a thermal balance in the engine is maintained at low power by transferring heat from the electrical generator to the fuel control to block the formation of ice in the fuel control'and to cool the electrical generator at low fuel flows.
At high power operation, as compared with low power operation, a large amount of heat per unit time is generated by engine components which are cooled by lubricating oil flowing through the engine through the engine oil system 44. A sudden reduction in power, such as decrease in power from cruise to flight idle, reduces the fuel flow through the first and second heat exchangers 74, 76 in the downstream portion of the fuel line. For a short period of time thereafter the large amount of heat that has built up in engine components and in the engine oil must be removed through the first heat exchanger 74 with the reduced fuel flow. As a result, the fuel temperature rapidly increases until it exceeds the temperature of the cooling fluid flowed in the cooling system 48 for the electrical generator 46.
This results in heat being transferred via the second heat exchanger 76 to the cooling fluid.
Thus, for a short period of time, the cooling fluid does not reject heat to the fuel but receives heat from fuel passing through the second heat exchanger. By employing the third heat exchanger 78, this heat from downstream portion of the fuel line is transferred back to the upstream portion of the fuel line from the cooling fluid. Transferring the heat back into the fuel minimizes the transient effect on the temperature and the heat capacity of the cooling fluid that results from the sudden reduction in power setting of the engine and has the beneficial effect on the fuel control and the filter outlined above. In addition use of the third heat exchanger reduces the feed during the transient period for using the fourtn heat exchanger with its inherent loss in engine efficiency to remove the heat from the cooling fluid.
Although the invention has been shown and described with respect to preferred embodiments thereof, it should be understood by those skilled in the art that various changes and omissions in the form and detail thereof may be made therein without departing from the spirit and the scope of the invention.
Claims (10)
1. A method for maintaining a thermal balance in a gas turbine engine operating at variable operating conditions and burning fuel to produce power wherein the fuel in the fuel supply system is at a temperature which is lower than the freezing point of water by reason of the fuel storage conditions, wherein fuel consumption is controlled by a fuel control and excess heat is produced by another component, the method
including the step of:
transferring excess heat from said component to the fuel flowing through the fuel control to inhibit the formation of ice in the fuel control and to cool the component.
2. The method for maintaining a thermal balance as claimed in claim 1 wherein the excess heat producing component is an electrical generator for producing electrical power which is driven by the gas turbine engine.
3. The method for maintaining a thermal balance as claimed in claim 2 wherein the step of transferring heat from the electrical generator to the fuel control includes the step recirculating a portion of the fuel flowed through the fuel control from a point in the fuel supply system downstream of the fuel control to a point in the fuel supply system upstream of the fuel control and transferring heat from the electrical generator to the fuel being recirculated.
4. The method for maintaining a thermal
balance as claimed in claim 2 wherein the step of transferring heat from the electrical generator to the fuel control includes the step of circulating a
cooling fluid through the electrical generator and transferring heat from the cooling fluid to the
recirculated fuel.
5. A method for maintaining a thermal balance in an axial flow gas turbine engine operating at
low power and burning fuel to produce power.
wherein a fuel supply system is used to deliver fuel to the combustion chamber of the engine, wherein a fuel control in the fuel supply system is used to control the flow of fuel through the fuel supply system, wherein a heat exchanger in the fuel supply system downstream of the fuel control is used to cool oil circulated through the engine by rejecting heat from the oil to the fuel and wherein an electrical generator driven by the engine is used to produce electrical power and waste heat, including the steps of::
transferring heat from the electrical generator to a cooling fluid;
transferring heat between the cooling fluid and the fuel supply system at a point downstream of the engine oil heat exchanger;
recirculating a portion of the fuel flowing through the fuel control from a point between the engine oil heat exchanger and the fuel control to a point upstream of the fuel control;
transferring heat from the cooling fluid to the recirculated fuel;
wherein the effect on the cooling fluid temperature of transient heat transfer from the fuel downstream of the fuel control to the cooling fluid during sudden reductions in power is reduced by transferring heat from the cooling fluid to fuel upstream of the fuel control.
6. In a gas turbine engine of the type in which fuel consumption is controlled by a fuel control and in which excess heat is produced by an electrical generator driven by the engine, the improvement comprises:
means for transferring heat from the electrical generator to the fuel control
wherein the transfer of heat to the fuel controls inhibits the formation of ice in the fuel control and cools the electrical generator.
7. The gas turbine engine of claim 6 wherein the fuel control has an inlet and an outlet and wherein said means for transferring heat from the electrical generator to the fuel control, includes
a heat exchanger in heat transfer communication with the electrical generator,
a fuel pump for pressurizing fuel passing through the fuel control, and
a conduit for recirculating pressurized fuel which is in fuel communication with the outlet of the fuel control, the heat exchanger, and the inlet to the fuel control such that the fuel recirculated through the conduit receives heat from the electrical generator as it passes the heat exchanger and transfers heat to the fuel control as the fuel passes through the fuel control.
8. The gas turbine engine of claim 7 which further includes a hydraulic vane controller for positioning stator vanes in the engine, said hydraulic vane controller being in fluid communication with the conduit for recirculating pressurized fuel such that the hydraulic vane controller develops a hydraulic force in response to the flow of pressurized fuel and receives heat from the fuel.
9. A gas turbine engine of the turbofan type in which fuel consumption is controlled by a fuel control having intake and discharge openings for fuel, in which engine oil is used to lubricate engine bearings and in which an electrical generator producing electrical power produces excess heat and is cooled by a cooling fluid
wherein the improvement comprises:
1. a fuel supply system which includes
1 a. an upstream portion in fluid communication
with the inlet of the fuel control, and
1 b. a downstream portion in fluid communication
with the outlet of the fuel control, the
downstream portion including
1 bi. a first heat exchanger in fluid
communication with the downstream
portion of the fuel line for transferring
heat from the engine oil to the fuel.
1 bii. a second heat exchanger in fluid
communication with the downstream
portion of the fuel line for transferring
heat between the cooling fluid and the
fuel; 2: A fuel recirculation system which includes
2a. a conduit for recirculating pressurized fuel
which extends between the downstream
portion of the fuel supply system and the
upstream portion of the fuel supply system,
2b. a hydraulic vane controller in fluid
communication with the fuel recirculation
conduit,
2c. a third heat exchanger in fluid
communication with the fuel recirculation
conduit for transferring heat from the cooling
fluid to the recirculated fuel and 3. a cooling system for the electrical generator
which includes
3a. a fourth heat exchanger for transferring
heat from the cooling fluid to fan air, and
3b. a conduit for cooling fluid it fluid and heat
transfer communication with the electrical
generator, the fourth heat exchanger, the
third heat exchanger, and the second heat
exchanger; wherein the third heat exchanger transfers heat from the cooling fluid to fuel in the upstream portion of the fuel supply system to minimize the transient effect of the heat transferred from the engine oil to the cooling fluid through the first and second heat exchangers in the downstream portion of the fuel line during a sudden reduction in the power setting of the engine.
10. The gas turbine engine of claim 7 or claim 8 which includes a filter upstream of the fuel control and wherein the recirculated fuel passes through the filter before entering the fuel control such that heat transferred to the filter blocks the accretion of wax-like paraffin on the filter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8206536A GB2095756B (en) | 1982-03-05 | 1982-03-05 | Balancing the heat flow between components associated with a gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8206536A GB2095756B (en) | 1982-03-05 | 1982-03-05 | Balancing the heat flow between components associated with a gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB2095756A true GB2095756A (en) | 1982-10-06 |
| GB2095756B GB2095756B (en) | 1985-01-16 |
Family
ID=10528806
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8206536A Expired GB2095756B (en) | 1982-03-05 | 1982-03-05 | Balancing the heat flow between components associated with a gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2095756B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2527266A1 (en) * | 1982-05-19 | 1983-11-25 | Kloeckner Humboldt Deutz Ag | GAS TURBINE PROPELLER FOR MISSILE |
| FR2536842A1 (en) * | 1982-11-29 | 1984-06-01 | Gen Electric | ENGINE LUBRICATING OIL HEAT RECOVERY SYSTEM AND METHOD OF RECOVERING SAID HEAT |
| WO2002016743A1 (en) * | 2000-08-22 | 2002-02-28 | Hamilton Sundstrand Corporation | Integrated thermal management and coolant system for an aircraft |
| WO2005061874A1 (en) * | 2003-12-20 | 2005-07-07 | Mtu Aero Engines Gmbh | Gas turbine comprising a generator cooled by kerosene |
| FR2914365A1 (en) * | 2007-03-28 | 2008-10-03 | Airbus France Sas | Equipment e.g. electric generator, cooling and controlling system for propulsion system i.e. jet engine, of aircraft, has closed circuit circulating heat transfer fluid between equipments and two heat exchange units |
| FR2944216A1 (en) * | 2009-04-14 | 2010-10-15 | Snecma | METHOD FOR DETECTING A CRISPING STATUS OR MAINTENANCE NEED FOR A TURBOMACHINE FUEL CIRCUIT |
| EP3054127A1 (en) * | 2015-02-09 | 2016-08-10 | United Technologies Corporation | Thermal management systems for gas turbine engines |
| EP2587024A3 (en) * | 2011-10-31 | 2017-01-18 | United Technologies Corporation | Gas turbine engine thermal management system |
| EP3144623A3 (en) * | 2015-09-21 | 2017-06-21 | Hamilton Sundstrand Corporation | Heat exchanger and cooling system for generator electronics cooling |
| EP3246545A1 (en) * | 2016-05-05 | 2017-11-22 | Rolls-Royce Corporation | System and method for stabilizing transcritical air-to-fuel heat exchange |
| US10400671B2 (en) | 2011-10-31 | 2019-09-03 | United Technologies Corporation | Gas turbine engine thermal management system |
-
1982
- 1982-03-05 GB GB8206536A patent/GB2095756B/en not_active Expired
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2527266A1 (en) * | 1982-05-19 | 1983-11-25 | Kloeckner Humboldt Deutz Ag | GAS TURBINE PROPELLER FOR MISSILE |
| FR2536842A1 (en) * | 1982-11-29 | 1984-06-01 | Gen Electric | ENGINE LUBRICATING OIL HEAT RECOVERY SYSTEM AND METHOD OF RECOVERING SAID HEAT |
| GB2131094A (en) * | 1982-11-29 | 1984-06-13 | Gen Electric | Engine oil heat recovery system |
| WO2002016743A1 (en) * | 2000-08-22 | 2002-02-28 | Hamilton Sundstrand Corporation | Integrated thermal management and coolant system for an aircraft |
| US6415595B1 (en) | 2000-08-22 | 2002-07-09 | Hamilton Sundstrand Corporation | Integrated thermal management and coolant system for an aircraft |
| WO2005061874A1 (en) * | 2003-12-20 | 2005-07-07 | Mtu Aero Engines Gmbh | Gas turbine comprising a generator cooled by kerosene |
| WO2008132400A3 (en) * | 2007-03-28 | 2009-02-12 | Airbus France | System for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft |
| WO2008132400A2 (en) * | 2007-03-28 | 2008-11-06 | Airbus France | System for cooling and adjusting the temperature of apparatuses in the propulsion assembly of an aircraft |
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| FR2944216A1 (en) * | 2009-04-14 | 2010-10-15 | Snecma | METHOD FOR DETECTING A CRISPING STATUS OR MAINTENANCE NEED FOR A TURBOMACHINE FUEL CIRCUIT |
| WO2010119215A1 (en) * | 2009-04-14 | 2010-10-21 | Snecma | Method for detecting an icing condition of or the need for servicing a fuel circuit of a turbine engine |
| JP2012523545A (en) * | 2009-04-14 | 2012-10-04 | スネクマ | How to detect a frozen state or maintenance need in a turbomachine fuel circuit |
| EP2587024A3 (en) * | 2011-10-31 | 2017-01-18 | United Technologies Corporation | Gas turbine engine thermal management system |
| US10400671B2 (en) | 2011-10-31 | 2019-09-03 | United Technologies Corporation | Gas turbine engine thermal management system |
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| EP3144623A3 (en) * | 2015-09-21 | 2017-06-21 | Hamilton Sundstrand Corporation | Heat exchanger and cooling system for generator electronics cooling |
| EP3246545A1 (en) * | 2016-05-05 | 2017-11-22 | Rolls-Royce Corporation | System and method for stabilizing transcritical air-to-fuel heat exchange |
| US10890114B2 (en) | 2016-05-05 | 2021-01-12 | Rolls-Royce Corporation | System and method for stabilizing transcritical air-to-fuel heat exchange |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2095756B (en) | 1985-01-16 |
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| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20010305 |