CN111765062A - High-low pressure combination formula fuel pump structure - Google Patents
High-low pressure combination formula fuel pump structure Download PDFInfo
- Publication number
- CN111765062A CN111765062A CN202010526618.7A CN202010526618A CN111765062A CN 111765062 A CN111765062 A CN 111765062A CN 202010526618 A CN202010526618 A CN 202010526618A CN 111765062 A CN111765062 A CN 111765062A
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- Prior art keywords
- fuel pump
- pressure
- low
- pressure fuel
- bearing
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B23/00—Pumping installations or systems
- F04B23/04—Combinations of two or more pumps
- F04B23/08—Combinations of two or more pumps the pumps being of different types
- F04B23/12—Combinations of two or more pumps the pumps being of different types at least one pump being of the rotary-piston positive-displacement type
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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
- 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
- F02C7/236—Fuel delivery systems comprising two or more pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B23/00—Pumping installations or systems
- F04B23/04—Combinations of two or more pumps
- F04B23/08—Combinations of two or more pumps the pumps being of different types
- F04B23/14—Combinations of two or more pumps the pumps being of different types at least one pump being of the non-positive-displacement type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B53/00—Component parts, details or accessories not provided for in, or of interest apart from, groups F04B1/00 - F04B23/00 or F04B39/00 - F04B47/00
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Rotary Pumps (AREA)
Abstract
The invention belongs to the field of aviation fuel pumps, and particularly relates to a high-low pressure combined fuel pump structure; the high-low pressure combined fuel pump adopts a mode of combining the centrifugal pump and the gear pump, the low-pressure stage fuel pump is used as a transmission tail end, and the low-pressure stage fuel pump and the high-pressure stage fuel pump are in connection transmission through the spline shaft, so that the strength design requirement of the shaft is reduced while the compactness of the structure is ensured; the high-pressure fuel pump adopts a composite bearing support mode, so that the overall weight is effectively reduced, and the radial force of the bearing is effectively reduced by introducing high-pressure oil into the gear cavity in the transition region; the problem of breakage caused by local compression of the sealing ring is solved by arranging the pressure equalizing groove in the sealing groove of the bearing outer ring; the problem of fuel backflow between a high-pressure fuel pump and a low-pressure fuel pump is solved by utilizing a spherical sealing structure and a static pressure oil film theory. The low-pressure fuel pump and the high-pressure fuel pump are integrated, so that the volume of the two-stage fuel pump is reduced, the weight is reduced, and the power-to-weight ratio is improved.
Description
Technical Field
The invention belongs to the field of aviation fuel pumps, and particularly relates to a high-low pressure combined fuel pump structure.
Background
In the field of the existing aviation fuel pumps, a low-pressure fuel pump and a high-pressure fuel pump are generally in split structures, and along with the continuous improvement of the performance requirements of a new generation of aviation engines, higher requirements are provided for fuel power devices, and integration and lightweight become important directions for the development of the aviation fuel pumps.
Disclosure of Invention
The technical problem solved by the invention is as follows: the high-low pressure combined fuel pump structure has the advantages of small volume, light weight and large power-weight ratio.
The technical scheme of the invention is as follows: a high-low pressure combined fuel pump structure for aviation is characterized in that a high-pressure fuel pump is used as a transmission input end, a low-pressure fuel pump is used as a transmission tail end, the input end is externally connected with a transmission shaft 1 and connected with the high-pressure fuel pump, the high-pressure fuel pump and the low-pressure fuel pump are connected and transmitted through a spline shaft 7, a driving gear 18 and a driven gear 4 of the high-pressure fuel pump are connected and transmitted through a driving fixed thrust bearing 19, a driving floating eccentric bearing 17 and a driving fixed bearing 15, the driven fixed thrust bearing 3, the driven floating eccentric bearing 5 and the driven fixed bearing 6 are supported, a spring A16 pushes a driving floating eccentric bearing 17 to be tightly attached to a driving gear 18, a closed impeller 13 is adopted for supplying oil to the low-pressure fuel pump, an impeller shaft 8 is supported through a ball bearing A12 and a ball bearing B14, and a spherical sealing assembly consisting of a ball baffle 10 and a ball seat 11 is sealed between the high-pressure fuel pump and the low-pressure fuel pump.
The high-pressure oil action end face 20 of the active floating eccentric bearing 17 is provided with an oil through hole A22.
The outer circumferential surfaces of the driving fixed thrust bearing 19, the driving fixed bearing 15, the driven fixed thrust bearing 3 and the driven fixed bearing 5 are provided with sealing grooves 23, and the bottoms of the grooves are provided with pressure equalizing grooves 24.
The pressing force between the ball stop 10 and the ball seat 11 is controlled by a spring B9.
The working spherical surface of the ball stop 10 is provided with an oil through hole B25 and an oil groove 26.
And a sealing ring 2 is arranged in the sealing groove 23.
Under the working running state of the ball stop 10 and the ball seat 11, a stable oil film with certain bearing capacity is formed on the working surface of the friction pair.
The pressure equalizing groove 24 is communicated with a high-pressure oil way.
A combination method of high-low pressure combination fuel pumps is characterized in that a transmission shaft 1 is externally connected to an input end of the combination fuel pump and serves as torque input, a spline shaft 7 serves as a connection structure of a high-pressure-level fuel pump and a low-pressure-level fuel pump, extracted power of the high-pressure-level fuel pump and extracted power of the low-pressure-level fuel pump are superposed and converted into load borne by the transmission shaft 1 externally connected to the input end, and extracted power of the low-pressure-level fuel.
The invention has the beneficial effects that: the high-low pressure combined fuel pump adopts a mode of combining a centrifugal pump and a gear pump, and the low-pressure stage fuel pump is used as a transmission tail end, so that the oil path structure is simplified; the low-pressure fuel pump and the high-pressure fuel pump are in connection transmission through the spline shaft, so that the strength design requirement of the shaft is reduced while the compactness of the structure is ensured; the high-pressure fuel pump adopts a composite bearing support mode, so that the overall weight is effectively reduced, and the radial force of the bearing is effectively reduced by introducing high-pressure oil into the gear cavity in the transition region; the problem of breakage caused by local compression of the sealing ring is solved by arranging the pressure equalizing groove in the sealing groove of the bearing outer ring; the problem of fuel backflow between a high-pressure fuel pump and a low-pressure fuel pump is solved by utilizing a spherical sealing structure and a static pressure oil film theory. The low-pressure fuel pump and the high-pressure fuel pump are integrated, so that the volume of the two-stage fuel pump is reduced, the weight is reduced, and the power-to-weight ratio is improved.
Drawings
FIG. 1 is a diagram: high-low pressure fuel combination pump assembly structure sketch map
FIG. 2 is a diagram of: active floating eccentric bearing sectional view and front view
FIG. 3 is a diagram of: schematic structural diagram of bearing sealing groove of high-pressure fuel pump with pressure equalizing groove
FIG. 4 is a diagram of: cross-sectional and front views of a spherical seal assembly
In the figure: the device comprises a base, a transmission shaft, a driven floating eccentric bearing, a driven fixed bearing, a driven gear, a driven floating eccentric bearing, a spline shaft, an impeller shaft, a spring B, a ball stop and a ball seat, wherein 1 is an input end externally connected with the transmission shaft, 2 is a sealing ring, 3 is the driven fixed thrust bearing, 4 is the driven gear, 5 is the driven floating eccentric bearing, 6 is the driven fixed bearing, 7 is the spline shaft, 8 is the; 12 is a ball bearing A, 13 is a closed impeller, 14 is a ball bearing B, 15 is a driving fixed bearing, 16 is a spring A, 17 is a driving floating eccentric bearing, 18 is a driving gear, 19 is a driving fixed thrust bearing, 20 is a high-pressure oil action end face, 21 is a driving floating eccentric bearing end face, 22 is an oil through hole A, 23 is a seal groove, 24 is a pressure equalizing groove, 25 is an oil through hole B, and 26 is an oil groove.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
the high-low pressure fuel combination pump consists of a low pressure level fuel pump and a high pressure level fuel pump, the schematic diagram of the assembly structure is shown in figure 1, the input end is externally connected with a transmission shaft 1 and connected with the high pressure level fuel pump, the high pressure level fuel pump and the low pressure level fuel pump are connected and driven through a spline shaft 7, a driving gear 18 and a driven gear 4 of the high pressure level fuel pump pass through a driving fixed thrust bearing 19, a driving floating eccentric bearing 17 and a driving fixed bearing 15, driven fixed thrust bearing 3, driven eccentric bearing 5 and the support of driven fixed bearing 6 float, spring A16 is used for promoting the eccentric bearing 17 of initiative float and pastes closely in driving gear 18, solve the end face leakage problem that the eccentric bearing end face 21 wearing and tearing of initiative float lead to, low pressure level fuel pump adopts closed impeller 13 fuel feeding, impeller shaft 8 supports through ball bearing A12 and ball bearing B14, adopt the sphere seal assembly who comprises ball fender 10 and ball seat 11 to seal between high, low pressure level fuel pump.
The high-pressure oil action end face 20 of the active floating eccentric bearing 17 is provided with an oil through hole A22 for introducing back high-pressure oil into the high-pressure and low-pressure transition region gear cavity, so as to achieve the purpose of balancing the radial hydraulic acting force of the gear pump bearing.
The outer circumferential surfaces of the driving fixed thrust bearing 19, the driving fixed bearing 15, the driven fixed thrust bearing 3 and the driven fixed bearing 5 are provided with sealing grooves 23, the bottoms of the grooves are provided with pressure equalizing grooves 24, the structure is communicated with a high-pressure oil path, the sealing of the outer circumferential surface of the bearing is ensured, and the problem of breakage caused by the fact that high-pressure oil directly acts on the local part of the sealing ring 2 is solved.
A combination method of high-low pressure combination fuel pumps is characterized in that a transmission shaft 1 is externally connected to an input end to serve as torque input, a spline shaft 7 serves as a connection structure of a high-pressure fuel pump and a low-pressure fuel pump, the problem of difficulty in strength design caused by a single transmission shaft is solved, the extracted power of the high-pressure fuel pump and the extracted power of the low-pressure fuel pump are superposed and converted into a load borne by the transmission shaft 1 externally connected to the input end, the extracted power of the low-pressure fuel pump is converted into a load borne by the spline shaft 7, and shear stress, resultant torque and tooth surface pressure stress load.
The spherical sealing assembly consisting of the ball retainer 10 and the ball seat 11 is adopted, so that the problem of fuel backflow between the high-pressure fuel pump and the low-pressure fuel pump is solved. The pressing force between the ball stop 10 and the ball seat 11 is controlled by a spring B9, an oil through hole B25 and an oil groove 26 are arranged on the working spherical surface of the ball stop 10, the design adopts the oil film supporting theory, the ball stop 10 is provided with an outer spherical working surface, the ball seat 11 is provided with an inner spherical working surface, and the two working surfaces are matched with each other to form a friction pair with certain density. A stable oil film with certain bearing capacity is formed on the working surfaces of the friction pair of the ball retainer 10 and the ball seat 11 in a working running state, on one hand, the surface of the friction pair is lubricated and cooled, the working environment of the friction pair is optimized, on the other hand, the contact surface of the friction pair is supported, the contact force between the two working surfaces of the friction pair is reduced, and the working load of the friction pair is reduced.
Claims (9)
1. A high-low pressure combined fuel pump structure for aviation is characterized in that a high-pressure fuel pump is used as a transmission input end, a low-pressure fuel pump is used as a transmission tail end, a transmission shaft (1) is externally connected with the input end and is connected with the high-pressure fuel pump, the high-pressure fuel pump and the low-pressure fuel pump are connected and transmitted through a spline shaft (7), a driving gear (18) and a driven gear (4) of the high-pressure fuel pump are supported through a driving fixed thrust bearing (19), a driving floating eccentric bearing (17), a driving fixed bearing (15), a driven fixed thrust bearing (3), a driven floating eccentric bearing (5) and a driven fixed bearing (6), a spring A (16) pushes the driving floating eccentric bearing (17) to be attached to the driving gear (18), the low-pressure fuel pump adopts a closed impeller (13) for supplying oil, an impeller shaft (8) is supported through a, the high-pressure fuel pump and the low-pressure fuel pump are sealed by a spherical sealing assembly consisting of a ball stop (10) and a ball seat (11).
2. The combined fuel pump structure for aircraft according to claim 1, wherein the high-pressure oil application end face (20) of the active floating eccentric bearing (17) is provided with an oil passage hole a (22).
3. The combined fuel pump structure for aviation use according to claim 1, wherein the outer circumferential surfaces of the driving fixed thrust bearing (19), the driving fixed bearing (15), the driven fixed thrust bearing (3) and the driven fixed bearing (5) are provided with sealing grooves (23), and the bottom of the groove is provided with a pressure equalizing groove (24).
4. Combined fuel pump construction for aircraft according to claim 1, characterized in that the pressing force between the ball stop (10) and the ball seat (11) is controlled by a spring B (9).
5. The combined fuel pump structure for aviation use according to claim 1, wherein the ball stopper (10) has an oil through hole B (25) and an oil groove (26) on its working spherical surface.
6. A combined fuel pump structure for aviation use according to claim 3, wherein the seal groove (23) is provided with a seal ring (2) therein.
7. The combined fuel pump structure for aviation use according to claim 1, wherein the ball retainer (10) and the ball seat (11) form a stable oil film with a certain bearing capacity on the working surface of the friction pair in the operating state.
8. The combined high and low pressure fuel pump structure for aircraft according to claim 3, wherein the pressure equalizing groove (24) communicates with a high pressure oil passage.
9. The combination method of the combined fuel pump structures for aviation use according to claims 1-8, characterized in that the input end is externally connected with the transmission shaft (1) as torque input, the spline shaft (7) is used as a connection structure of the high-pressure fuel pump and the low-pressure fuel pump, the extracted power of the high-pressure fuel pump and the extracted power of the low-pressure fuel pump are superposed and converted into the load of the input end externally connected with the transmission shaft (1), and the extracted power of the low-pressure fuel pump is converted into the load of the spline shaft (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010526618.7A CN111765062B (en) | 2020-06-10 | 2020-06-10 | High-low pressure combination formula fuel pump structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010526618.7A CN111765062B (en) | 2020-06-10 | 2020-06-10 | High-low pressure combination formula fuel pump structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111765062A true CN111765062A (en) | 2020-10-13 |
| CN111765062B CN111765062B (en) | 2022-10-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010526618.7A Active CN111765062B (en) | 2020-06-10 | 2020-06-10 | High-low pressure combination formula fuel pump structure |
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| Country | Link |
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| CN (1) | CN111765062B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114320884A (en) * | 2021-11-10 | 2022-04-12 | 浙江环誉泵业科技有限公司 | High-speed high-temperature high-efficiency fuel pump for aerospace |
| CN114962206A (en) * | 2022-06-09 | 2022-08-30 | 湖南高创翔宇科技有限公司 | Graded pressurizing fuel pump |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2870719A (en) * | 1955-10-04 | 1959-01-27 | Thompson Prod Inc | Bushing for pressure loaded gear pump having a tapered journal surface |
| US2957418A (en) * | 1957-01-28 | 1960-10-25 | William V Edwards | Gear fuel pump |
| US20050232784A1 (en) * | 2004-04-19 | 2005-10-20 | Yates Martin K | Pump assembly |
| CN202188125U (en) * | 2011-02-25 | 2012-04-11 | 西华大学 | Spherical mechanical sealing device |
| CN103452838A (en) * | 2012-06-04 | 2013-12-18 | 霍尼韦尔国际公司 | Gear pump, pumping apparatus including the same, and aircraft fuel system including gear pump |
| CN203441486U (en) * | 2013-09-16 | 2014-02-19 | 中国地质大学（武汉） | Hydraulic vibration head for sonic drilling |
| CN105465372A (en) * | 2016-01-26 | 2016-04-06 | 成都一通密封股份有限公司 | Large-deflection self-adaptive seal for low-speed equipment |
| CN106415011A (en) * | 2014-04-15 | 2017-02-15 | 赛峰飞机发动机公司 | Fuel gear pump intended, in particular, as a high-pressure pump |
| CN107100933A (en) * | 2017-04-13 | 2017-08-29 | 南方科技大学 | A kind of realizing active sealing formula aerostatic bearing |
-
2020
- 2020-06-10 CN CN202010526618.7A patent/CN111765062B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2870719A (en) * | 1955-10-04 | 1959-01-27 | Thompson Prod Inc | Bushing for pressure loaded gear pump having a tapered journal surface |
| US2957418A (en) * | 1957-01-28 | 1960-10-25 | William V Edwards | Gear fuel pump |
| US20050232784A1 (en) * | 2004-04-19 | 2005-10-20 | Yates Martin K | Pump assembly |
| CN202188125U (en) * | 2011-02-25 | 2012-04-11 | 西华大学 | Spherical mechanical sealing device |
| CN103452838A (en) * | 2012-06-04 | 2013-12-18 | 霍尼韦尔国际公司 | Gear pump, pumping apparatus including the same, and aircraft fuel system including gear pump |
| CN203441486U (en) * | 2013-09-16 | 2014-02-19 | 中国地质大学（武汉） | Hydraulic vibration head for sonic drilling |
| CN106415011A (en) * | 2014-04-15 | 2017-02-15 | 赛峰飞机发动机公司 | Fuel gear pump intended, in particular, as a high-pressure pump |
| CN105465372A (en) * | 2016-01-26 | 2016-04-06 | 成都一通密封股份有限公司 | Large-deflection self-adaptive seal for low-speed equipment |
| CN107100933A (en) * | 2017-04-13 | 2017-08-29 | 南方科技大学 | A kind of realizing active sealing formula aerostatic bearing |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114320884A (en) * | 2021-11-10 | 2022-04-12 | 浙江环誉泵业科技有限公司 | High-speed high-temperature high-efficiency fuel pump for aerospace |
| CN114962206A (en) * | 2022-06-09 | 2022-08-30 | 湖南高创翔宇科技有限公司 | Graded pressurizing fuel pump |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111765062B (en) | 2022-10-14 |
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