CN107023401A - A kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve and its application method - Google Patents
A kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve and its application method Download PDFInfo
- Publication number
- CN107023401A CN107023401A CN201710396114.6A CN201710396114A CN107023401A CN 107023401 A CN107023401 A CN 107023401A CN 201710396114 A CN201710396114 A CN 201710396114A CN 107023401 A CN107023401 A CN 107023401A
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- oil
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- 239000000446 fuel Substances 0.000 title claims abstract description 36
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims description 7
- 239000003921 oil Substances 0.000 claims abstract description 111
- 239000000295 fuel oil Substances 0.000 claims abstract description 28
- 238000007789 sealing Methods 0.000 claims description 17
- 239000002184 metal Substances 0.000 claims description 7
- 230000015572 biosynthetic process Effects 0.000 claims description 5
- 244000309464 bull Species 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 10
- 230000035611 feeding Effects 0.000 description 7
- 239000007921 spray Substances 0.000 description 3
- 238000000889 atomisation Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000003344 environmental pollutant Substances 0.000 description 2
- 231100000719 pollutant Toxicity 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000003595 mist Substances 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
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention discloses a kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve, including case, one-level valve system and two grades of valve systems.The present invention is associated with the scope of oil pressure using the size of every grade of valve, and metastable fuel delivery can be also controlled when oil pressure is excessive, not fuel feeding when oil pressure is too small, so as to ensure that the fuel oil of nozzle ejection is constant；Using pure mechanic structure is used, security reliability and maintainability are greatly increased；Controlled simultaneously using two-stage valve, it is ensured that the accuracy of fuel delivery.
Description
Technical field
The present invention relates to Aero-Space engine fuel injection system technical field, specifically a kind of aero-engine fuel oil
Nozzle pre-combustion grade auxiliary oil circuit valve and its application method.
Background technology
Aero-engine is described as " heart " of aircraft, and combustion chamber is engine " heart ", its same compressor, turbine
Three big core components of aeropropulsion system are constituted together.Combustion chamber pair will be by inlet duct, burner inner liner, housing, nozzle and point
The basic building blocks such as firearm are constituted.Fuel nozzle is one of most secondary part wanted in combustion chamber, and its function is, by fuel-oil atmozation, to accelerate mixed
Close gas to be formed, it is ensured that stable burning and raising efficiency of combustion.But it is to ensure that the pressure and flow of the fuel oil for reaching fuel nozzle
Relative constancy, it is necessary to which the valve of advanced configuration ensures.Guarantee engine and gas-turbine combustion chamber, fuel-oil atmozation quality,
Liquid mist evaporation, movement locus and fuel concentration distribution have significant impact to combustion chamber property indices.Atomization quality is poor, concentration
Skewness, the inappropriate grade of spray cone angle is also by the life-span for directly affecting combustion chamber and turbine and the discharge of pollutant, especially
It is that ground gas turbine nozzle atomization quality influences very big to pollutant emission.Show for this reason, it may be necessary to which R ＆ D design is a kind of new
The valve for changing fuel nozzle oil supply system of generationization high-precision control, can come the high accuracy and height that complete high-precision fuel nozzle
By property.
The content of the invention
It is an object of the invention to provide a kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve and its use
Method, to solve the problems mentioned in the above background technology.
To achieve the above object, the present invention provides following technical scheme：
A kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve, including case, one-level valve system and two grades
Valve system；The case includes external standard snap joint, shell and auxiliary oil circuit oil pipe, one-level valve system and two grades of valve
System is installed in the inside of case；External standard snap joint include the extraneous quick termination of standard size, cylindrical shell and
Inner chamber；Shell includes the secondary shell of cylinder, step inner cavity and auxiliary oil circuit hole, and step inner cavity is located at the inside of the secondary shell of cylinder,
Auxiliary oil circuit hole is connected through one end of the secondary shell of cylinder with step inner cavity；The one-level valve system is included into oil screen pad
Piece, metal wire knitted are entered oil screen, oil-feed end cap, one-level valve body, oil sealing, one-level valve plug, one-level bourdon tube, spring and adjusted
Whole pad, cylinder body base, collar pad and valve body sealing ring, it is cylindrical that one-level valve body includes body, oil suction chamber, smooth seal
Angle, body chamber and seal groove, oil sealing and one-level valve plug by groove constitute one, one-level valve plug also include inlet hole and
Inner chamber；Two grades of valve systems include two grades of valve plugs, valve fork clip circle, valve end cap, valve body, two grades of bullets beyond the Great Wall
Spring, valve cylinder and valve bottom, two grades of valve plugs include termination, shelves groove, bar portion, go out oil groove and baffle ring, valve cylinder include body,
Oil suction chamber, two-stage oil feeding hole and seal groove.
It is used as further scheme of the invention：The extraneous quick termination of the standard size is arranged at the termination of cylindrical shell
At position, inner chamber is located at the inside of cylindrical shell.
The application method of aviation engine fuel nozzle pre-combustion grade auxiliary oil circuit valve in more than one technical schemes：Including
Following steps：
A, external standard snap joint and fuel feed pump interlink, and fuel oil enters from the inner chamber of external standard snap joint,
Enter oil screen by metal wire knitted to reach at one-level valve system；
B, oil pressure effect under, oil pressure to oil sealing formation pressure, compress one-level bourdon tube, make one-level valve body and
Leave to form gap so that by fuel oil, fuel oil reaches inner chamber by the inlet hole of one-level valve plug again between oil sealing；
C, the fuel oil gone out from the inner chamber of one-level valve plug continue, to two grades of valve plug formation pressure, to compress two-level spring, from
And fuel gallery is formed, fuel oil enters from the two-stage oil feeding hole of valve cylinder again, and the fuel oil of auxiliary oil circuit is gone out from auxiliary oil circuit oil outlet
Reach auxiliary oil circuit oil pipe；In the case where oil pressure persistently increases, continue to compress two-level spring, reach the lower annular groove of two grades of valve plugs
To valve cylinder smallest end and gap is formed so that fuel oil passes through, enter finally into auxiliary oil circuit oil pipe and reach fuel nozzle and eject
Burning.
Compared with prior art, the beneficial effects of the invention are as follows：
1st, using there is two-stage valve control structure in same housing；
2nd, it is associated all with the scope of oil pressure using the size of every grade of valve, it can also be controlled when oil pressure is excessive metastable
Fuel delivery, not fuel feeding when oil pressure is too small, so as to ensure that the fuel oil that nozzle sprays is constant；
3rd, using pure mechanic structure is used, security reliability and maintainability are greatly increased；
4th, controlled simultaneously using two-stage valve, it is ensured that the accuracy of fuel delivery.
Brief description of the drawings
Fig. 1 is principle schematic diagram of the invention；
Fig. 2 is the structural representation of case in the present invention；
Fig. 3 is the principle schematic diagram of external standard snap joint in the present invention；
Fig. 4 is the principle schematic diagram of shell in the present invention；
Fig. 5 is the principle schematic diagram of one-level valve system in the present invention；
Fig. 6 is the principle schematic diagram of oil-feed end cap in the present invention；
Fig. 7 is the principle schematic diagram of the oily component of worry in the present invention；
Fig. 8 is the principle schematic diagram of one-level valve plug and Oil sealing assembly in the present invention；
Fig. 9 is the principle schematic diagram of two grades of valve systems in the present invention；
Figure 10 is the principle schematic diagram of valve body and valve cylinder sleeve in the present invention；
Figure 11 is the principle schematic diagram of two grades of valve plugs in the present invention.
In figure：1- cases, 2- one-levels valve system, bis- grades of valve systems of 3-, the external standard snap joints of 4-, 5- shells,
6- auxiliary oil circuits oil pipe, 7- enter oil screen pad, 8- metal wire knitteds and enter oil screen, 9- end caps, 10- one-levels valve body, 11- oil
Envelope, 12- one-level valve plug, 13- one-levels bourdon tube, 14- springs adjusting pad, 15- cylinder bodies base, 16- collars pad, 17- valve shells
Body sealing ring, bis- grades of valve plugs of 18-, bis- grades of valve plugs of 19-, 20- valve fork clips circle, 21- valve end cap, bis- grades of bullets of 22- beyond the Great Wall
Spring, 23- valve bodies, 24- valve cylinder, 25- object staffs cun extraneous quick termination, 26- cylindrical shells, 27- inner chambers, 28- cylinders
Shape pair shell, 29- step inner cavities, 30- auxiliary oil circuits hole, 31- bodies, 32- oil suction chambers, 33- smooth seals bull nose, 34- bodies
Chamber, 35- seal grooves, 36- grooves, 37- fuel feed holes, 38- inner chambers, 39- two-stage oil feedings hole, 40- oil suction chambers, 41- seal grooves,
42- terminations, 43- shelves grooves, 44- bar portions, 45- go out oil groove, 46- baffle rings.
Embodiment
The technical scheme of this patent is described in more detail with reference to embodiment.
Refer to Fig. 1-11, a kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve, including case 1, one-level
Valve system 2 and two grades of valve systems 3；The case 1 includes external standard snap joint 4, shell 5 and auxiliary oil circuit oil pipe 6, one
Level valve system 2 and two grades of valve systems 3 are installed in the inside of case 1；External standard snap joint 4 is included outside standard size
The quick termination 25 in boundary, cylindrical shell 26 and inner chamber 27；Shell 5 includes the secondary shell 28 of cylinder, step inner cavity 29 and auxiliary oil circuit
Hole 30, step inner cavity 29 located at the inside of the secondary shell 28 of cylinder, auxiliary oil circuit hole 30 through one end of the secondary shell 28 of cylinder with
Step inner cavity 29 is connected；The one-level valve system 2 includes entering oil screen 8, oil inlet end into oil screen pad 7, metal wire knitted
Lid 9, one-level valve body 10, oil sealing 11, one-level valve plug 12, one-level bourdon tube 13, spring adjusting pad 14, cylinder body base 15,
Collar pad 16 and valve body sealing ring 17, one-level valve body 10 include body 31, oil suction chamber 32, smooth seal bull nose
33rd, body chamber 34 and seal groove 35, oil sealing 11 and one-level valve plug 12 constitute one by groove 36, and one-level valve plug 12 is also
Including inlet hole 37 and inner chamber 38；Two grades of valve systems 3 include two grades of valve plugs 18, valve fork clip circle 19, valve beyond the Great Wall
End cap 20, valve body 21, two-level spring 22, valve cylinder 23 and valve bottom 24, two grades of valve plugs 18 include termination 42, shelves groove
43rd, bar portion 44, go out oil groove 45 and baffle ring 46, valve cylinder 24 includes body 23, oil suction chamber 40, two-stage oil feeding hole 39 and seal groove
41。
The extraneous quick termination 25 of the standard size is arranged at the tip position of cylindrical shell 26, and inner chamber 27 is located at circle
The inside of cylindrical outer cover 26.
The application method of aviation engine fuel nozzle pre-combustion grade auxiliary oil circuit valve in more than one technical schemes：Including
Following steps：
A, external standard snap joint 4 interlink with fuel feed pump, and fuel oil enters from the inner chamber 27 of external standard snap joint 4
Enter, entering oil screen 8 by metal wire knitted reaches at one-level valve system 2；
B, under the pressure effect of oil, oil pressure makes one-level valve shell to the formation pressure of oil sealing 11, compression one-level bourdon tube 13
Leave to form gap so that by fuel oil, fuel oil reaches interior by the inlet hole 37 of one-level valve plug 12 again between body 10 and oil sealing 11
Chamber 38；
C, the fuel oil gone out from the inner chamber 38 of one-level valve plug 12 continue, to two grades of formation pressure of valve plug 18, to compress two grades of bullets
Spring 22, so as to form fuel gallery, fuel oil enters from the two-stage oil feeding hole 39 of valve cylinder 23 again, and the fuel oil of auxiliary oil circuit is from auxiliary oil circuit
Oil outlet 45 goes out to reach auxiliary oil circuit oil pipe 6；In the case where oil pressure persistently increases, continue to compress two-level spring 22, make two grades
The lower annular groove 46 of valve plug 18 reaches the smallest end of valve cylinder 23 and forms gap so that fuel oil passes through, and enters finally into auxiliary oil circuit oil
Pipe 7 reaches fuel nozzle and ejects burning.
The present invention, which is used in same housing, two-stage valve control structure；Model using the size of every grade of valve all with oil pressure
Enclose associated, metastable fuel delivery can be also controlled when oil pressure is excessive, not fuel feeding when oil pressure is too small, so as to ensure that nozzle sprays
Fuel oil it is constant；Using pure mechanic structure is used, security reliability and maintainability are greatly increased；Using the same time control of two-stage valve
System, it is ensured that the accuracy of fuel delivery.
The better embodiment to this patent is explained in detail above, but this patent is not limited to above-mentioned embodiment party
, can also be on the premise of this patent objective not be departed from formula, the knowledge that one skilled in the relevant art possesses
Make a variety of changes.
Claims (3)
1. a kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve, it is characterised in that lived including case (1), one-level
Door system (2) and two grades of valve systems (3)；The case (1) includes external standard snap joint (4), shell (5) and auxiliary oil circuit
Oil pipe (6), one-level valve system (2) and two grades of valve systems (3) are installed in the inside of case (1)；External standard quickly connects
Head (4) includes the extraneous quick termination (25) of standard size, cylindrical shell (26) and inner chamber (27)；Shell (5) includes cylinder
Secondary shell (28), step inner cavity (29) and auxiliary oil circuit hole (30), step inner cavity (29) located at the inside of the secondary shell (28) of cylinder,
Auxiliary oil circuit hole (30) is connected through one end of the secondary shell (28) of cylinder with step inner cavity (29)；The one-level valve system (2)
Enter oil screen (8), oil-feed end cap (9), one-level valve body (10), oil sealing including entering oil screen pad (7), metal wire knitted
(11), one-level valve plug (12), one-level bourdon tube (13), spring adjusting pad (14), cylinder body base (15), collar pad (16) and work
Door shell body sealing ring (17), one-level valve body (10) include body (31), oil suction chamber (32), smooth seal bull nose (33),
Body chamber (34) and seal groove (35), oil sealing (11) and one-level valve plug (12) constitute one by groove (36), and one-level is lived
Men Sai (12) also includes inlet hole (37) and inner chamber (38)；Two grades of valve systems (3) include two grades of valve plugs (18), valve
Fork clip circle (19), valve end cap (20), valve body (21), two-level spring (22), valve cylinder (23) and valve bottom beyond the Great Wall
(24), two grades of valve plugs (18) include termination (42), shelves groove (43), bar portion (44), go out oil groove (45) and baffle ring (46), valve cylinder
(24) body (23), oil suction chamber (40), two-stage oil feeding hole (39) and seal groove (41) are included.
2. aero-engine fuel nozzle according to claim 1 pre-combustion grade auxiliary oil circuit valve, it is characterised in that described
The extraneous quick termination (25) of standard size is arranged at the tip position of cylindrical shell (26), and inner chamber (27) are outer located at cylinder
The inside of shell (26).
3. a kind of aero-engine fuel nozzle as described in claim 1-2 is any is with the user of pre-combustion grade auxiliary oil circuit valve
Method, it is characterised in that comprise the following steps：
A, external standard snap joint (4) interlink with fuel feed pump, and fuel oil is from the inner chamber (27) of external standard snap joint (4)
Into entering oil screen (8) by metal wire knitted and reach one-level valve system (2) place；
B, oil pressure effect under, oil pressure to oil sealing (11) formation pressure, compression one-level bourdon tube (13), make one-level valve shell
Leave to form gap so that by fuel oil, fuel oil passes through the inlet hole of one-level valve plug (12) again between body (10) and oil sealing (11)
(37) inner chamber (38) is reached；
C, the fuel oil gone out from the inner chamber (38) of one-level valve plug (12) continue to form pressure to two grades of valve plugs (18), compress two grades
Spring (22), so as to form fuel gallery, fuel oil enters from the two-stage oil feeding hole (39) of valve cylinder (23) again, the fuel oil of auxiliary oil circuit
Go out to reach auxiliary oil circuit oil pipe (6) from auxiliary oil circuit oil outlet (45)；In the case where oil pressure persistently increases, continue to compress two grades of bullets
Spring (22), makes the lower annular groove (46) of two grades of valve plugs (18) reach valve cylinder (23) smallest end and forms gap so that fuel oil is logical
Cross, enter finally into auxiliary oil circuit oil pipe (7) arrival fuel nozzle and eject burning.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710396114.6A CN107023401A (en) | 2017-05-28 | 2017-05-28 | A kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve and its application method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710396114.6A CN107023401A (en) | 2017-05-28 | 2017-05-28 | A kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve and its application method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107023401A true CN107023401A (en) | 2017-08-08 |
Family
ID=59528938
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710396114.6A Pending CN107023401A (en) | 2017-05-28 | 2017-05-28 | A kind of aero-engine fuel nozzle pre-combustion grade auxiliary oil circuit valve and its application method |
Country Status (1)
| Country | Link |
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| CN (1) | CN107023401A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112254170A (en) * | 2020-10-20 | 2021-01-22 | 中国航发沈阳发动机研究所 | Improved sealing structure of auxiliary oil way fuel nozzle valve |
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| US4326377A (en) * | 1980-01-18 | 1982-04-27 | Rockwell International Corporation | Injection shut-off valve for regenerative injection |
| DE3912106A1 (en) * | 1988-05-02 | 1989-11-16 | Volkswagen Ag | Fuel injection device |
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| US6446613B1 (en) * | 2001-12-20 | 2002-09-10 | Stanadyne Corporation | Two-stage pressure limiting valve |
| FR2832492A1 (en) * | 2001-11-20 | 2003-05-23 | Snecma Moteurs | IMPROVEMENTS TO TURBOMACHINE INJECTORS |
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| CN101230987A (en) * | 2007-01-22 | 2008-07-30 | 伊斯帕诺-絮扎公司 | Two-stage fuel injector |
| CN101684751A (en) * | 2008-09-22 | 2010-03-31 | 贵州红林机械有限公司 | Fuel cut-off valve of reheat fuel control unit of turbofan engine |
| US20110041805A1 (en) * | 2009-08-20 | 2011-02-24 | Delavan Inc | System and method for locking retention of valve components |
| CN102175045A (en) * | 2010-12-31 | 2011-09-07 | 北京航空航天大学 | Low-emission combustion chamber with main combustible stage head part multi-point slant oil taking |
| FR3003014A1 (en) * | 2013-03-05 | 2014-09-12 | Snecma | COMPACT DOSING DEVICE FOR TWO FUEL CIRCUIT INJECTOR, PREFERABLY FOR AIRCRAFT TURBOMACHINE |
| EP3048368A1 (en) * | 2015-01-26 | 2016-07-27 | Delavan, Inc. | Dynamic valve seal having retaining features |
-
2017
- 2017-05-28 CN CN201710396114.6A patent/CN107023401A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR521173A (en) * | 1920-07-26 | 1921-07-07 | Hippolyte Saintagne | Oil filter |
| GB288321A (en) * | 1927-04-05 | 1929-02-07 | Hans Holzwarth | Combined fuel and air admission device for oil explosion turbines |
| SU69241A1 (en) * | 1945-12-26 | 1946-11-30 | В.Н. Свободов | Fuel pump discharge valve |
| US4326377A (en) * | 1980-01-18 | 1982-04-27 | Rockwell International Corporation | Injection shut-off valve for regenerative injection |
| DE3912106A1 (en) * | 1988-05-02 | 1989-11-16 | Volkswagen Ag | Fuel injection device |
| US5732730A (en) * | 1995-09-11 | 1998-03-31 | Delavan Inc | Combined check valve and metering valve assembly |
| FR2832492A1 (en) * | 2001-11-20 | 2003-05-23 | Snecma Moteurs | IMPROVEMENTS TO TURBOMACHINE INJECTORS |
| US6446613B1 (en) * | 2001-12-20 | 2002-09-10 | Stanadyne Corporation | Two-stage pressure limiting valve |
| CN1661269A (en) * | 2004-02-25 | 2005-08-31 | 沃尔沃建造设备控股（瑞典）有限公司 | Pilot operated relief valve |
| CN101230987A (en) * | 2007-01-22 | 2008-07-30 | 伊斯帕诺-絮扎公司 | Two-stage fuel injector |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112254170A (en) * | 2020-10-20 | 2021-01-22 | 中国航发沈阳发动机研究所 | Improved sealing structure of auxiliary oil way fuel nozzle valve |
| CN112254170B (en) * | 2020-10-20 | 2022-06-07 | 中国航发沈阳发动机研究所 | Improved sealing structure of auxiliary oil way fuel nozzle valve |
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Effective date of registration: 20191030 Address after: 201100 No. 3998, South Lianhua Road, Minhang District, Shanghai Applicant after: China Hangfa commercial aviation engine limited liability company Address before: 710000, No. 6, Jing Wei Industrial Park, 1 middle section of Jing Gao Bei Road, Jinghe new town, Xi'an Economic Development Zone, Shaanxi, China Applicant before: Xi'an established Aviation Manufacturing Co., Ltd. |