CN110529251A - A kind of parallel combustion chambers turboaxle motor - Google Patents
A kind of parallel combustion chambers turboaxle motor Download PDFInfo
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- CN110529251A CN110529251A CN201910778118.XA CN201910778118A CN110529251A CN 110529251 A CN110529251 A CN 110529251A CN 201910778118 A CN201910778118 A CN 201910778118A CN 110529251 A CN110529251 A CN 110529251A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 83
- 239000007789 gas Substances 0.000 claims abstract description 87
- 210000004209 hair Anatomy 0.000 claims abstract description 47
- 239000002737 fuel gas Substances 0.000 claims abstract description 28
- 230000008676 import Effects 0.000 claims description 37
- 230000008450 motivation Effects 0.000 claims description 16
- 239000000567 combustion gas Substances 0.000 claims description 15
- 230000007246 mechanism Effects 0.000 claims description 5
- 230000008901 benefit Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 25
- 239000000446 fuel Substances 0.000 description 14
- 238000010304 firing Methods 0.000 description 12
- 239000002912 waste gas Substances 0.000 description 5
- 230000007423 decrease Effects 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000005119 centrifugation Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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- 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
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
-
- 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
- F02C3/103—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 the compressor being of the centrifugal type
-
- 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
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- 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
- F02C6/02—Plural gas-turbine plants having a common power output
-
- 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
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of parallel combustion chambers turboaxle motors, belong to aero-engine whirlpool axis type.The invention is constructed using the turboshaft engine of parallel combustion chambers, has preferably played the function of power turbine, is improved fuel gas temperature before power turbine, is improved the power to weight ratio of engine on the whole, be a kind of novel turboshaft engine.Engine drives compressor rotation, another way enters after parallel combustion chambers burning to power turbine expansion work, drives the rotation of the department enclosures such as rotor by by airflow diversion after compressor, entering all the way after this hair combustion chambers burn to gas turbine expansion work.Parallel combustion chambers can form the characteristics of multiple shared parallel combustion chambers, have the advantages that a variety of, be widely used in large and medium-sized helicopter as power device, it can also be used to which jet dynamic control or gas turbine ship power use.
Description
Technical field
The invention belongs to aero-engine-turboaxle motor fields, and in particular to a kind of parallel combustion chambers turbine wheel shaft hair
Motivation.
Background technique
The turboaxle motor that world man the helo uses at present is essentially the structure type that tandem type has power turbine,
Basic principle block diagram such as Fig. 1 (solid line indicates gas circuit in figure, and dotted line indicates that machine driving, subsequent figure equally indicate), air enters
Air intake duct carries out compression by compressor and improves air pressure, then burnt by combustion chamber, forms the combustion of high temperature and pressure
Gas turbine expansion work is passed through in gas, combustion gas, drives compressor rotation, the pressure and temperature of at this moment combustion gas has a degree of
It reduces, but also there is very high enthalpy, combustion gas drives rotor and other portions of helicopter attached using power turbine expansion work
Part, temperature and pressure further decreases after at this moment combustion gas expansion, by emission by exhaust pipe into atmosphere.
The tandem type turboaxle motor form of this structure has obtained mature application, but for power turbine and
Speech, by the expansion work of front gas turbine, temperature and pressure has very big decline for combustion gas, and do work reduced capability.But
On the one hand in order to protect gas turbine, the high-temperature high-pressure fuel gas temperature behind combustion chamber cannot be excessively high, and another aspect power turbine can
To select material and structure as gas turbine, but at this moment fuel gas temperature has been far smaller than the receiving limit of power turbine
System, power turbine cannot be not fully exerted.
In order to enable power turbine can preferably do work, has the knot for a combustion chamber of connecting again after gas turbine
Structure carries out secondary fuel injection burning, to improve fuel gas temperature before power turbine, basic principle block diagram such as Fig. 2, this second-time burning
Form can improve turboshaft engine output power, and fuel consumption increase can receive by verifying well.But this
The construction of kind combustion chambers in tandem, on the one hand since gas pressure has already passed through primary reduction, so that efficiency of combustion is greatly reduced, separately
Contain the exhaust gas of a large amount of primary combustions in the gas of one side second-time burning, so that the stability of burning reduces.
Summary of the invention
In order to preferably play the function of power turbine, fuel gas temperature before power turbine is improved, the present invention provides a kind of new
Type parallel combustion chambers turboaxle motor.
According to the first embodiment of the present invention, a kind of parallel combustion chambers turboaxle motor, including a son are provided
Engine and a sustainer, in which:
Sub- engine include sub- engine compressor (may include two stage compressor, i.e. diagonal flow type compressor and centrifugal
Compressor), sub- engine chamber, sub- engine gas turbine, sub- engine exhaust；
Second engine includes engine collecting pipe, sustainer chamber, main engine power turbine, sustainer row
Air flue.
Sub- engine inlets connexon engine compressor (may include two stage compressor, i.e., diagonal flow type compressor and
Centrifugal-flow compressor), blower outlet is divided into two-way, all the way the import of connexon engine chamber, and sub- engine chamber goes out
Mouthful connexon engine gas turbine (may include two-stage turbine, i.e. high pressure turbine guide vane and low-pressure fuel gas turbine), combustion gas whirlpool
Wheel outlet connexon engine exhaust；
Another way connects engine collecting pipe, and collecting pipe connects sustainer chamber, sustainer chamber's connection master
Engine power turbine, main engine power turbine connection sustainer exhaust duct, the output axis connection retarder of power turbine,
Retarder connects rotor.
The working principle of the parallel combustion chambers turboaxle motor of first embodiment are as follows: air enters sub- engine
Air intake duct is divided into two-way after the pressurization of sub- engine compressor, passes through sub- engine chamber mixed fuel firing all the way
Afterwards, it does work, is rotated by power shaft band mover engine compressor, exhaust gas starts by son to sub- engine gas turbine expansion
Machine exhaust duct is discharged into atmosphere；Another way enters sustainer chamber's mixed fuel firing in parallel by engine collecting pipe
Afterwards, it does work into main engine power turbine expansion, the department enclosures such as retarder and subsequent rotor is driven by power output shaft
Rotation, sustainer burning waste gas are discharged into atmosphere by sustainer exhaust duct.
According to the second embodiment of the present invention, a kind of double hair turboshaft engines of parallel combustion chambers, including two are provided
A sub- engine and a sustainer, wherein
First sub- engine includes that the first sub- engine compressor (the first compressor) (may include two stage compressor, i.e.,
Diagonal flow type compressor and centrifugal-flow compressor), the first engine chamber, the first gas turbine (the first sub- engine gas whirlpool
Wheel, generally include high pressure turbine guide vane and low-pressure fuel gas turbine), the first engine exhaust (the first sub- engine exhaust)；
Second sub- engine includes the second compressor (the second sub- engine compressor), the second engine chamber, second
Gas turbine (the second sub- engine gas turbine, may include high pressure turbine guide vane and low-pressure fuel gas turbine), the second engine
Exhaust duct (the second engine exhaust)；
Sustainer includes engine collecting pipe, sustainer chamber, main engine power turbine, sustainer exhaust
Road；
Wherein, the air intake duct of the first sub- engine connects the first compressor, and the first blower outlet is divided into two-way, connects all the way
The first combustion chamber import is connect, the first combustor exit connects the first turbine, and the first turbine outlet connects first row air flue, another way
Connect engine collecting pipe, collecting pipe connects sustainer chamber's import, sustainer chamber outlet connection sustainer
Turbine, sustainer turbine connect sustainer exhaust duct, the output axis connection retarder of power turbine, retarder connection rotation
The wing；
The air intake duct of second sub- engine connects the second compressor, and the second blower outlet is divided into two-way, connects all the way
Two combustion chamber imports, the second combustor exit connect the second turbine, and the second turbine outlet connects second row air flue, and another way is the same as the
One sub- engine equally connects engine collecting pipe.
The working principle of the double hair turboshaft engines of the parallel combustion chambers of second embodiment are as follows: air respectively enters first
Respectively it is divided into two-way after sub- engine respectively compressor pressure with the second sub- engine inlets, compressed air passes through all the way
It after crossing sub- engine chamber mixed fuel firing, does work to sub- engine gas turbine expansion, is sent out by power shaft band mover
The rotation of motivation compressor, exhaust gas are discharged into atmosphere by sub- engine exhaust；Another way compressed air passes through engine collecting pipe
It is merged together into sustainer chamber's mixed fuel firing in parallel, high-temperature high-pressure fuel gas enters main engine power whirlpool
Expansion work is taken turns, the rotation of the department enclosures such as retarder and subsequent rotor, sustainer burning waste gas are driven by power output shaft
Atmosphere is discharged by sustainer exhaust duct.
According to the third embodiment the present invention, a kind of hair of parallel combustion chambers three turboshaft engine, including three are provided
Sub- engine and a sustainer, wherein
First sub- engine includes the first engine inlets, the first compressor, the first engine chamber, the first combustion gas
Turbine (may include high pressure turbine guide vane and low-pressure fuel gas turbine), the first engine exhaust；
Second sub- engine includes the second engine inlets, the second compressor, the second engine chamber, the second combustion gas
Turbine (may include high pressure turbine guide vane and low-pressure fuel gas turbine), the second engine exhaust；
The sub- engine of third includes third engine inlets, third compressor, third engine chamber, third combustion gas
Turbine (may include high pressure turbine guide vane and low-pressure fuel gas turbine), third engine exhaust；
Sustainer includes engine collecting pipe, sustainer chamber, main engine power turbine, sustainer exhaust
Road；
The air intake duct of first sub- engine connects the first compressor, and the first blower outlet is divided into two-way, connects all the way
One engine chamber import, the first gas turbine of the first engine chamber outlet connection, the first gas turbine outlet connection
First engine exhaust, another way connect sustainer chamber's import, combustor exit connection by engine collecting pipe
Main engine power turbine, power turbine connect sustainer exhaust duct, the output axis connection retarder of power turbine, retarder
Connect rotor；
The air intake duct of second sub- engine connects the second compressor, and the second blower outlet is divided into two-way, connects all the way
The import of engine with two combustion chamber, the second gas turbine of the second engine chamber outlet connection, the second gas turbine outlet connection
Second engine exhaust, another way pass through as the first engine engine collecting pipe connect sustainer chamber into
Mouthful；
The air intake duct of the sub- engine of third connects third compressor, and third blower outlet is divided into two-way, connects all the way
The import of trimotor combustion chamber, third combustor exit connect third gas turbine, third gas turbine outlet connection third hair
Motivation exhaust duct, another way pass through the connection sustainer chamber's import of engine collecting pipe as the first engine.
The working principle that the parallel combustion chambers three of above-mentioned third embodiment send out turboshaft engine is: air respectively enters
First, second, and third sub- engine inlets are respectively divided into two-way, all the way after sub- engine respectively compressor pressure
Compressed air does work to sub- engine gas turbine expansion, passes through power after sub- engine chamber mixed fuel firing
Axis band mover engine compressor rotates, and exhaust gas is discharged into atmosphere by sub- engine exhaust；Another way compressed air is by hair
Motivation collecting pipe is merged together into sustainer chamber's mixed fuel firing in parallel, and high-temperature high-pressure fuel gas enters main hair
Motivation power turbine expansion work drives the rotation of the department enclosures such as retarder and subsequent rotor by power output shaft, and master starts
Machine burning waste gas is discharged into atmosphere by sustainer exhaust duct.
The present invention using parallel combustion chambers turboshaft engine construct, by taking second embodiment as an example, air enter into
Air flue is divided into two-way after compressor pressure, all the way after combustion chambers burn, to gas turbine expansion work, band dynamic pressure
Mechanism of qi rotation, exhaust gas are discharged into atmosphere by exhaust duct, and another way does power turbine expansion after combustion chambers burn in parallel
Function, drives the rotation of the department enclosures such as rotor, and exhaust gas is discharged into atmosphere by exhaust duct.
The characteristics of this parallel combustion chambers is, the work treatment of gas turbine and power turbine be it is reciprocity, adjusting is only
It is vertical, the advantage that have:
1, fuel gas temperature before power turbine can be greatly improved, the acting ability of power turbine is increased；
2, the shortcomings that tandem combustion chamber will not occur；
3, independent is become for the adjusting of gas turbine and power turbine, so that engine control is more easier, it more can be same
When meet the working condition requirement of compressor and rotor；
4, multiple coordinated control can be preferably realized；
5, independent combustion chamber can use new configuration, improve efficiency of combustion；
6, power turbine can use bigger diameter, reduce revolving speed while improving torque, be conducive to improve power whirlpool
Efficiency is taken turns, and reduces the size of subsequent retarder.
The turboaxle motor of this parallel combustion chambers may increase the complexity of structure for single-shot helicopter
Property, but for double hairs, for the helicopters such as three hairs, this configuration reduces integrally-built complexity, and can be well
Multi-engined operation is matched, while improving power, simplifies structure, there is very high application value.Such as double
Hair and three hairs, more multiple principle is similar, is fired before entering power turbine after air pressure share split after multiple compressor being come out confluence
Burn room.Furthermore multiple parallel combustion chambers engine (can also be used for jet dynamic control in driven generator or other line loads
Or the use of gas turbine ship power) in, it can also be widely used.
Detailed description of the invention
Fig. 1 is general turboshaft engine functional block diagram.
Fig. 2 is combustion chambers in tandem turboshaft engine functional block diagram.
Fig. 3 is parallel combustion chambers turboshaft engine functional block diagram according to the first embodiment of the present invention.
Fig. 4 is parallel combustion chambers turboaxle motor structural schematic diagram according to the first embodiment of the present invention.
Fig. 5 is the double hair turboshaft engine functional block diagrams of parallel combustion chambers according to the second embodiment of the present invention.
Fig. 6 is the double hair turboaxle motor structural representations of parallel combustion chambers according to the second embodiment of the present invention
Figure.
Fig. 7 is the hair turboshaft engine functional block diagram of parallel combustion chambers three according to the third embodiment the present invention.
Fig. 8 is the hair turboshaft engine structural schematic diagram of parallel combustion chambers three according to the third embodiment the present invention.
Fig. 9 is that preceding output type is laid out schematic diagram in double hairs.
Figure 10 is that output type is laid out schematic diagram after double hairs are outer.
Figure 11 is that preceding output type is laid out schematic diagram in three hairs.
Figure 12 is that output type is laid out schematic diagram after three hairs are outer.
Appended drawing reference:
1- engine inlets (or first engine inlets)；2- inclined flow air compressor；3- centrifugal compressor；4- hair
Motivation combustion chamber (or first engine chamber)；5- high pressure turbine guide vane；6- low-pressure fuel gas turbine；7- engine exhaust
(or first engine exhaust)；8- engine collecting pipe；9- sustainer cyclone；The sustainer chamber 10-；11- master
Engine chamber flameholder；12- main engine power stators；13- main engine power turbine rotor；14- master
Engine exhaust (is located at power output shaft)；15- check valve；16- compressor shunts guide ring；1 '-the second engine charge
Road；2 '-inclined flow air compressors；3 '-centrifugal compressors；4 '-the second engine chambers；5 ' high pressure turbine guide vanes；6 '-low-pressure fuel gas
Turbine；7 '-the second engine exhausts；1 "-third engine inlets；2 "-inclined flow air compressors；3 "-centrifugal compressors；4"-
Third engine chamber；5 "-high pressure turbine guide vanes；6 "-low-pressure fuel gas turbines；7 "-third engine exhausts.
Specific embodiment
The present invention is further illustrated below in conjunction with attached drawing.
Fig. 3 shows the functional block diagram of the parallel combustion chambers turboaxle motor of an embodiment according to the present invention,
Wherein, sub- engine inlets connexon engine compressor (can with and be preferably provided with two stage compressor, diagonal flow type compressor and
Centrifugal-flow compressor), blower outlet is divided into two-way, all the way connexon engine chamber (combustion chamber 2 in figure) import, son
Engine chamber outlet connexon engine gas turbine (can with and be preferably provided with two-stage turbine, i.e. high-pressure turbine and low pressure
Turbine), gas turbine exports the connexon exhaust pipe of engine；Another way connects sustainer chamber through engine collecting pipe
(combustion chamber 1 in figure), sustainer chamber connect main engine power turbine, and main engine power turbine connection master starts
Machine exhaust duct, the output axis connection retarder of power turbine, retarder connect rotor.
Fig. 4 shows the structural schematic diagram of the parallel combustion chambers turboaxle motor according to the embodiment above comprising
Sub- engine and sustainer,
Sub- engine includes sub- engine compressor, is two stage compressor, i.e., diagonal flow type compressor 2 and centrifugal calms the anger
Machine 3, sub- engine chamber 4, sub- engine gas turbine (including high pressure turbine guide vane 5 and low-pressure fuel gas turbine 6), son start
Machine exhaust duct 7；
Second engine includes engine collecting pipe 8, sustainer chamber 10, main engine power turbine (including master
Engine power stators 12；Main engine power turbine rotor 13), sustainer exhaust duct 14 and power output shaft, hair
The junction of motivation collecting pipe 8 and sustainer chamber 10 is equipped with sustainer cyclone 9,
Wherein, (two stage compressor can be set, diagonal flow type is calmed the anger in sub- 1 connexon engine compressor of engine inlets
Machine 2 and centrifugal-flow compressor 3), blower outlet is divided into two-way, all the way 4 import of connexon engine chamber, sub- engine combustion
Burn room 4 export connexon engine gas turbine (may include two-stage turbine, i.e. high pressure turbine guide vane 5 and low-pressure fuel gas turbine
6), gas turbine exports connexon engine exhaust 7；
Another way connects engine collecting pipe 8 (check valve 15 is equipped in it), and collecting pipe 8 connects sustainer chamber 10
(inside is equipped with sustainer chamber's flameholder 11), sustainer chamber 10 connect main engine power turbine (packet
Include main engine power stators 12 and main engine power turbine rotor 13), main engine power turbine connection master starts
Machine exhaust duct and power output shaft 14, the output shaft of power turbine go connection retarder (not shown), and retarder connects rotor (not
Diagram).
When work, air enters sub- engine inlets 1, after sub- engine compressor (2,3) pressurization, is divided into two
Road, to sub- engine gas turbine (5,6) expansion work, passes through all the way after sub- 4 mixed fuel firing of engine chamber
Power shaft band mover engine compressor (2,3) rotates, and exhaust gas is discharged into atmosphere by sub- engine exhaust 7；Another way is passed through
After engine collecting pipe 8 enters 10 mixed fuel firing of sustainer chamber in parallel, into main engine power turbine
(12,13) expansion work drives the rotation of the department enclosures such as retarder and subsequent rotor, sustainer burning by power output shaft
Exhaust gas is discharged into atmosphere by sustainer exhaust duct.
Fig. 5 shows the functional block diagram of the double hair turboshaft engines of parallel combustion chambers, wherein 1 air intake duct of engine connection hair
The compressor of motivation 1, the blower outlet are divided into two-way, connect 1 combustion chamber import of engine, combustor exit connection all the way
The gas turbine of engine 1, gas turbine outlet connection exhaust duct, the another way master intermediate by the connection of engine collecting pipe
Engine chamber import, sustainer chamber outlet connection power turbine, power turbine connect exhaust duct, power turbine
Axis connection retarder is exported, retarder connects rotor；
2 air intake duct of engine connects the compressor of engine 2, which is divided into two-way, connects engine 2 all the way
Combustion chamber import, the combustor exit connect engine 2 gas turbine, the gas turbine outlet connection exhaust duct, it is another
Road equally connects engine collecting pipe with engine 1.
Fig. 6 shows the structural schematic diagram of the double hair turboshaft engines of parallel combustion chambers, including two sub- engines and one
Sustainer, wherein
First sub- engine includes that sub- engine compressor (the first compressor) (including two stage compressor: calm the anger by diagonal flow type
Machine 2 and centrifugal-flow compressor 3), sub- engine chamber (the first engine chamber) 4, sub- engine gas turbine (first combustion
Air turbine, including high pressure turbine guide vane 5 and low-pressure fuel gas turbine 6), sub- engine exhaust (the first engine exhaust) 7；
Second sub- engine includes that sub- engine compressor (calm the anger by the second compressor, including inclined flow air compressor 2 ' and centrifugation
Machine 3 '), sub- engine chamber (the second combustion chamber) 4 ', sub- engine gas turbine (the second gas turbine, including high-pressure gas
5 ' low-pressure fuel gas turbine of turbine；6 '), sub- engine exhaust (second row air flue) 7 '；
Sustainer includes engine collecting pipe 8 (check valve 15 is equipped in it), sustainer chamber 10, sustainer
Power turbine (including main engine power stators 12；Main engine power turbine rotor 13), sustainer exhaust duct 14,
The junction of engine collecting pipe 8 and sustainer chamber 10 is equipped with sustainer cyclone 9.
First sub- engine inlets 1 connect the first compressor (2,3), and the first blower outlet is divided into two-way, connects all the way
4 import of the first engine chamber is connect, the first combustor exit connects the first gas turbine (5,6), the outlet of the first gas turbine
First row air flue is connected, another way shunts the connection of guide ring 16 engine collecting pipe 8 via compressor, collecting pipe 8 connects main hair
10 import of motivation combustion chamber, the outlet of sustainer chamber 10 connection sustainer turbine (including main engine power turbine is quiet
Son 12 and main engine power turbine rotor 13), sustainer turbine connects sustainer exhaust duct 14, the output of power turbine
Axis connection retarder, retarder connect rotor；
Second sub- engine inlets 1 ' connect the second compressor (2 ', 3 '), and the second blower outlet is divided into two-way, all the way
Connect the 4 ' import of the second combustion chamber, the second combustion chamber 4 ' outlet connection the second turbine (5 ', 6 '), the second turbine outlet connection second
Engine exhaust 7 ', another way is the same with the first sub- engine to shunt the connection engine collecting pipe of guide ring 16 via compressor
8。
When work, air respectively enters the first and second sub- engine inlets 1,1 ', respectively calms the anger by sub- engine
After machine pressurization, respectively it is divided into two-way, after sub- 4 mixed fuel firing of engine chamber, antithetical phrase starts compressed air all the way
Machine gas turbine expansion work is rotated by power shaft band mover engine compressor (2,3), and exhaust gas passes through sub- engine exhaust
Road 7 is discharged into atmosphere；Another way compressed air is merged together by engine collecting pipe into sustainer chamber in parallel
10 mixed fuel firings, high-temperature high-pressure fuel gas enter main engine power turbine (12,13) expansion work, pass through power output shaft
The rotation of the department enclosures such as retarder and subsequent rotor is driven, sustainer burning waste gas is discharged into greatly by sustainer exhaust duct
Gas.
Fig. 7 shows the functional block diagram that parallel combustion chambers three send out turboshaft engine, wherein the air intake duct of engine 1 connects
Compressor, blower outlet are divided into two-way, connect 1 combustion chamber import of engine all the way, and combustor exit connects gas turbine, combustion
Air turbine outlet connection 1 exhaust pipe of engine, another way connect sustainer chamber's import, burning by engine collecting pipe
Room outlet connection main engine power turbine, power turbine connect sustainer exhaust pipe, and the output axis connection of power turbine subtracts
Fast device, retarder connect rotor；
The air intake duct of engine 2 connects compressor, and blower outlet is divided into two-way, connect all the way 2 combustion chamber of engine into
Mouthful, combustor exit connect gas turbine, gas turbine outlet connection 2 exhaust pipe of engine, another way such as the first engine that
Sample connects sustainer chamber's import by engine collecting pipe；
The air intake duct of engine 3 connects compressor, and blower outlet is divided into two-way, connect all the way 3 combustion chamber of engine into
Mouthful, 3 combustor exit of engine connects gas turbine, gas turbine outlet connection 3 exhaust pipe of engine, and another way such as first is sent out
Motivation passes through the connection sustainer chamber's import of engine collecting pipe like that.
Fig. 8 shows the structural schematic diagram that parallel combustion chambers three send out turboshaft engine, including three sub- engines and one
Sustainer, wherein
First sub- engine includes the first engine inlets 1, the first compressor (including two stage compressor: diagonal flow type pressure
Mechanism of qi 2 and centrifugal-flow compressor 3), the first engine chamber, the first gas turbine, the first engine exhaust；
Second sub- engine includes the second engine inlets 1 ', the second compressor (including two stage compressor: diagonal flow type pressure
Mechanism of qi 2 ' and centrifugal-flow compressor 3 '), the second engine chamber, the second gas turbine, the second engine exhaust；
The sub- engine of third includes third engine inlets 1 ", third compressor (including two stage compressor: diagonal flow type pressure
Mechanism of qi 2 " and centrifugal-flow compressor 3 "), third engine chamber, third gas turbine, third engine exhaust；
Sustainer includes engine collecting pipe 8 (check valve 15 is equipped in it), sustainer chamber 10, sustainer
Power turbine (including main engine power stators 12；Main engine power turbine rotor 13), sustainer exhaust duct 14,
The junction of engine collecting pipe 8 and sustainer chamber 10 is equipped with sustainer cyclone 9；
The air intake duct 1 of first sub- engine connects the first compressor (2,3), and the first blower outlet is divided into two-way, all the way
Connect 4 import of the first engine chamber, the first engine chamber outlet connection the first gas turbine (5,6), the first combustion gas
Turbine outlet connects the first engine exhaust 7, and another way shunts guide ring 16 via compressor and connected by engine collecting pipe 8
10 import of sustainer chamber is connect, combustor exit connects main engine power turbine (12,13), and power turbine connects main hair
Motivation exhaust duct 14, the output axis connection retarder of power turbine, retarder connect rotor；
The air intake duct 1 ' of second sub- engine connects the second compressor (2 ', 3 '), and the second blower outlet is divided into two-way, and one
Road connects the 4 ' import of the second engine chamber, and the second combustor exit connects the second gas turbine (5 ', 6 '), the second combustion gas whirlpool
The second engine exhaust 7 ' of wheel outlet connection, another way shunt guide ring 16 via compressor as the first engine and pass through
Engine collecting pipe connects sustainer chamber's import；
The air intake duct 1 " of the sub- engine of third connects third compressor (2 ", 3 "), and third blower outlet is divided into two-way, and one
Road connects the 4 " import of third engine chamber, third engine chamber outlet connection third gas turbine (5 ", 6 "), third
Gas turbine outlet connection third engine exhaust 7 ", another way shunt guide ring via compressor as the first engine
16 connect 10 import of sustainer chamber by engine collecting pipe 8.
When work, air respectively enters the first, second, and third sub- engine inlets 1,1 ', 1 ", by sub- engine
After respective compressor (2,3,2 ', 3 ', 2 ", 3 ") pressurization, respectively it is divided into two-way, compressed air passes through sub- engine chamber all the way
It after mixed fuel firing, does work to sub- engine gas turbine expansion, is rotated, given up by power shaft band mover engine compressor
Gas is discharged into atmosphere by sub- engine exhaust；Another way compressed air is merged together by engine collecting pipe into parallel
Sustainer chamber (10) mixed fuel firing, high-temperature high-pressure fuel gas enter main engine power turbine (12,13) expansion
Acting drives the rotation of the department enclosures such as retarder and subsequent rotor by power output shaft, and sustainer burning waste gas is by master
Engine exhaust is discharged into atmosphere.
Engine efficiency can be promoted there are also following some processing modes in the specific implementation process:
1, the guider of power turbine and rotor generally use non-cooled form at present, after parallel combustion chambers, due to
Fuel gas temperature greatly improves before power turbine, and the blade and rotor blade of power turbine guider are also required to cold using hollow air
But form will be reinforced in design to its blade, and wheel disc and the cooling of shell consider.
It 2, can be no longer using the ring cylinder being widely used at present for the rear preceding combustion chamber of output form power turbine after parallel connection
Shape form can be using whole tubular, using better diffused since there is no transmission shaft structures among combustion chamber.
Respective sub- engine also can reduce due to eliminating power turbine, corresponding chamber diameter, and subtract on the whole on the whole
The small size and quality of respective engine.
3, Cong Gefa compressor shunts the formal of bleed, this engine chamber air-flow is entered with conventional whirlpool axis hair
Motivation, to power turbine before the air-flow that supplies of burner introduced from the last level shunt of compressor, need to be arranged collector ring, diversion pipe
Road, mixing chamber, spin chamber etc..It is the difficult point that structure designs from respective bleed air, in order to further increase air pressure, collector
It needs with air deflector using cross section of fluid channel flaring form, to reduce loss, runner answers appropriate design transition.
4, the new form of power turbine, power turbine need to be improved turbine torque using multistage, major diameter form and dropped simultaneously
Low secondary speed can be further improved turbine efficiency and be conducive to reduce the size of subsequent retarder.
In addition, according to actual requirement, can divide in the turboshaft engine of double hairs in parallel or multiple (including three hairs) combustion chamber
For preposition output and the postposition way of output, it is only the needs for meeting different layouts that efficiency, which has no too big difference,.It is laid out schematic diagram
Such as Fig. 9, Figure 10, Figure 11, Figure 12, output type is laid out schematic diagram before wherein Fig. 9 is in double hairs, and Figure 10 is output type layout after double hairs are outer
Schematic diagram, Figure 11 be in three hairs before output type be laid out schematic diagram, Figure 12 is that output type is laid out schematic diagram after three hairs are outer, left arrow indicate into
Enter the air of engine, right side arrow indicates compressed high temperature and pressure air or high-temperature fuel gas.
Claims (9)
1. a kind of parallel combustion chambers turboaxle motor, including a sub- engine and a sustainer, it is characterised in that:
Sub- engine includes sub- engine compressor, sub- engine chamber, sub- engine gas turbine, sub- engine exhaust
Road；
Second engine includes engine collecting pipe, sustainer chamber, main engine power turbine, sustainer exhaust
Road.
Sub- engine inlets connexon engine compressor, blower outlet are divided into two-way, all the way connexon engine combustion
Room import, sub- engine chamber export connexon engine gas turbine, and gas turbine exports connexon engine exhaust；
Another way connects engine collecting pipe, and collecting pipe connects sustainer chamber, and sustainer chamber connection master starts
Mechanomotive force turbine, main engine power turbine connect sustainer exhaust duct, and the output axis connection retarder of power turbine slows down
Device connects rotor.
2. parallel combustion chambers turboaxle motor according to claim 1, which is characterized in that sub- engine compressor includes
The two stage compressor of diagonal flow type compressor and centrifugal-flow compressor.
3. parallel combustion chambers turboaxle motor according to claim 1 or 2, which is characterized in that sub- engine gas whirlpool
Wheel includes the two-stage turbine of high pressure turbine guide vane and low-pressure fuel gas turbine.
4. a kind of double hair turboshaft engines of parallel combustion chambers, including two sub- engines and a sustainer, wherein
First sub- engine includes the first compressor, the first engine chamber, the first gas turbine, the first engine exhaust
Road；
Second sub- engine includes the second compressor, the second engine chamber, the second gas turbine, the second engine exhaust
Road；
Sustainer includes engine collecting pipe, sustainer chamber, main engine power turbine, sustainer exhaust duct；
Wherein, the air intake duct of the first sub- engine connects the first compressor, and the first blower outlet is divided into two-way, connects all the way
One combustion chamber import, the first combustor exit connect the first turbine, and the first turbine outlet connects first row air flue, another way connection
Engine collecting pipe, collecting pipe connect sustainer chamber's import, and sustainer chamber outlet connects sustainer turbine,
Sustainer turbine connects sustainer exhaust duct, the output axis connection retarder of power turbine, and retarder connects rotor；
The air intake duct of second sub- engine connects the second compressor, and the second blower outlet is divided into two-way, connects the second combustion all the way
Room import is burnt, the second combustor exit connects the second turbine, and the second turbine outlet connects second row air flue, and another way is the same as the first son
Engine equally connects engine collecting pipe.
5. the double hair turboshaft engines of parallel combustion chambers according to claim 4, which is characterized in that the first, second compressor
It respectively include the two stage compressor of diagonal flow type compressor and centrifugal-flow compressor；And/or first gas turbine, the second combustion gas whirlpool
Wheel respectively includes the two-stage turbine of high pressure turbine guide vane and low-pressure fuel gas turbine.
6. the double hair turboshaft engines of parallel combustion chambers according to claim 4 or 5, which is characterized in that preceding output in double hairs
Output type layout after outside type or double hairs.
7. a kind of parallel combustion chambers three send out turboshaft engine, including three sub- engines and a sustainer, it is characterised in that:
First sub- engine includes the first engine inlets, the first compressor, the first engine chamber, the first combustion gas whirlpool
Wheel, the first engine exhaust；
Second sub- engine includes the second engine inlets, the second compressor, the second engine chamber, the second combustion gas whirlpool
Wheel, the second engine exhaust；
The sub- engine of third includes third engine inlets, third compressor, third engine chamber, third combustion gas whirlpool
Wheel, third engine exhaust；
Sustainer includes engine collecting pipe, sustainer chamber, main engine power turbine, sustainer exhaust duct；
The air intake duct of first sub- engine connects the first compressor, and the first blower outlet is divided into two-way, connects the first hair all the way
The import of motivation combustion chamber, the first gas turbine of the first engine chamber outlet connection, the first gas turbine outlet connection first
Engine exhaust, another way connect sustainer chamber's import by engine collecting pipe, and combustor exit connects main hair
Motivation power turbine, power turbine connect sustainer exhaust duct, the output axis connection retarder of power turbine, retarder connection
Rotor；
The air intake duct of second sub- engine connects the second compressor, and the second blower outlet is divided into two-way, connects the second hair all the way
The import of motivation combustion chamber, the second gas turbine of the second engine chamber outlet connection, the second gas turbine outlet connection second
Engine exhaust, another way pass through the connection sustainer chamber's import of engine collecting pipe as the first engine；
The air intake duct of the sub- engine of third connects third compressor, and third blower outlet is divided into two-way, connects third hair all the way
The import of motivation combustion chamber, third combustor exit connect third gas turbine, third gas turbine outlet connection third engine
Exhaust duct, another way pass through the connection sustainer chamber's import of engine collecting pipe as the first engine.
8. the double hair turboshaft engines of parallel combustion chambers according to claim 7, which is characterized in that the first, second, third pressure
Mechanism of qi respectively includes the two stage compressor of diagonal flow type compressor and centrifugal-flow compressor；And/or
First gas turbine, the second gas turbine, third gas turbine respectively include high pressure turbine guide vane and low-pressure fuel gas turbine
Two-stage turbine.
9. the double hair turboshaft engines of parallel combustion chambers according to claim 7 or 8, which is characterized in that turboshaft engine is
Output type layout after output type or three hairs are outer before in three hairs.
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Application publication date: 20191203 |