CN209743063U - Rich fuel gas conveying pipeline - Google Patents
Rich fuel gas conveying pipeline Download PDFInfo
- Publication number
- CN209743063U CN209743063U CN201920439730.XU CN201920439730U CN209743063U CN 209743063 U CN209743063 U CN 209743063U CN 201920439730 U CN201920439730 U CN 201920439730U CN 209743063 U CN209743063 U CN 209743063U
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- Prior art keywords
- turbine
- gas
- gas generator
- shell
- fuel
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Abstract
The utility model discloses a rich fuel gas conveying pipeline, which comprises a turbine, a turbine shell, a fuel gas generator and a turbine seat, wherein the turbine seat is arranged at the front end of the turbine, and the turbine shell is arranged at the periphery of the turbine at intervals; an annular turbine channel is arranged in the turbine shell, the gas generator comprises a gas generator bent pipe, the gas generator is connected with the turbine shell through the gas generator bent pipe, a nozzle is arranged at the connection position, and the nozzle is arranged in a tangent mode with the turbine shell; the inner surface of the turbine channel is tangentially provided with a plurality of gas outlets which are communicated with the turbine channel and the interior of the turbine shell. The utility model discloses be used for providing rich gas for air turbine rocket engine, can also provide the power source for the oxidizer delivery pump simultaneously.
Description
Technical Field
The utility model belongs to the technical field of aerospace, a fuel gas conveying pipeline is burnt to rich is related to.
Background
In recent years, the near space, which is the airspace between the satellite and the aircraft, is increasingly emphasized by the relevant countries. In order to solve the problem that the air in the space is thin and cannot meet the working requirement of the air-breathing engine, and to better utilize the space, the engine needs to be designed to work not only in the troposphere but also in the stratosphere. The concept of a combination engine is emerging. Because of this space, only the combined engine can fully meet the technical requirements of the hypersonic proximity spacecraft. Although the combined turbo-ramjet engine can meet the flight of the condition, the regulation technology of the air inlet and the exhaust and the structural thermal protection technology are difficult to solve. The air turbine rocket combined engine is particularly prominent. The key technology of the air turbine rocket engine aims to ensure starting under low speed, the turbocharging part better ensures starting under low speed, but a transmission shaft between a turbine and an oxidant delivery pump can generate additional bending moment due to non-uniformity of driving force to affect the service life. Achieving sufficient mixing of fuel and air is also an important research issue, so that the combined engine can generate enough thrust under a low-speed condition, and takeoff power of the combined engine in a low-speed stage is guaranteed.
air turbine rocket engines combine the advantages of both turbojet engines and rocket engines. The air turbine rocket engine utilizes oxygen in air to realize autonomous takeoff and landing of the aircraft in an aircraft airspace, and propellant carried by the air turbine rocket engine can enable the relevant aircraft to fly in the adjacent space. The design of the pipeline for supplying the rich fuel gas from the rich fuel gas generator is a key technology, and the fuel gas from the rich fuel gas generator only provides the rich fuel gas for the rocket engine, so that the utilization efficiency of the rich fuel gas is greatly reduced. In order to solve the problems, the fuel-rich gas conveying pipeline is designed to provide fuel-rich gas for the rocket engine and drive the turbine to drive the transmission shaft so as to provide power for the air pump, so that the utilization efficiency of the fuel-rich gas generator is greatly improved.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a fuel gas conveying pipeline of burning richly for provide the fuel gas of burning richly for air turbine rocket engine, can also provide the power source for the oxidizer delivery pump simultaneously.
the utility model adopts the technical proposal that: the utility model provides a rich fuel gas conveying pipeline, which comprises a turbine, a turbine shell, a fuel gas generator and a turbine seat, wherein the turbine seat is arranged at the front end of the turbine, and the turbine shell is arranged at the periphery of the turbine at intervals;
An annular turbine channel is arranged in the turbine shell, the gas generator comprises a gas generator bent pipe, the gas generator is connected with the turbine shell through the gas generator bent pipe, a nozzle is arranged at the connection position, and the nozzle is arranged in a tangent mode with the turbine shell;
the inner surface of the turbine channel is tangentially provided with a plurality of gas outlets which are communicated with the turbine channel and the interior of the turbine shell.
Preferably, the fuel-rich gas conveying pipeline further comprises a fuel gas demand part, and the fuel gas demand part is connected with the turbine housing through a first flange.
preferably, a gas nozzle is arranged between the gas demand part and the turbine casing.
preferably, the turbine housing and the turbine base are connected through a second flange.
Preferably, a transmission shaft is further connected to the turbine, extends through the turbine base to the outside of the turbine housing, and is connected to the oxidant delivery pump.
The utility model has the advantages that:
(1) The utility model provides a fuel-rich gas conveying pipeline for air turbine rocket engine provides fuel-rich gas, can also provide the power source for the oxidizer delivery pump simultaneously. The utility model relates to a fuel gas conveying line that richly fires not only provides the fuel gas that richly fires for rocket engine still to drive the turbine and drive the transmission shaft so that provide power for the air pump way, has just so improved fuel gas generator's utilization efficiency richly.
(2) When the gas generator drives the turbine, additional bending moment is easily caused on a transmission shaft between the turbine and the oxidant delivery pump, and the service life of the transmission shaft and the service life of a bearing are seriously influenced. The utility model discloses set up a plurality of gas outlet in the turbine passageway to even blowout drive turbine reduces additional moment of flexure, thereby reduces unnecessary fatigue damage.
(3) The turbine shell is internally provided with an annular turbine passage, so that the rich-fuel gas medium generated by the gas generator can uniformly drive each blade of the turbine, and the advantage of the uniform driving of the turbine is that the service life of a transmission shaft and a bearing between the turbine and the oxidant delivery pump can be prolonged.
(4) The fuel gas generator drives the turbine to rotate by continuously providing rich fuel gas, the nozzle at the elbow of the fuel gas generator is tangentially communicated with the turbine shell, and the rich fuel gas drives the turbine and transmits the rotation to the oxidant delivery pump through a transmission shaft between the turbine and the oxidant delivery pump.
(5) The turbine channel inside the turbine housing is designed as shown in fig. 6, and the gas outlets arranged at the same angle around the turbine channel facilitate the rich gas from the gas generator to uniformly drive the turbine, reduce the additional moment effect on the transmission shaft during rotation, and thus contribute to the increase of the service life of the transmission shaft.
Drawings
FIG. 1 is a schematic perspective view of a fuel-rich gas delivery pipeline provided by an embodiment of the present invention (a fuel gas requirement and an oxidant delivery pump are omitted);
Fig. 2 is a schematic front view structure diagram of a fuel-rich gas conveying pipeline provided by an embodiment of the present invention;
FIG. 3 is a schematic sectional view A-A of FIG. 2;
Fig. 4 is a rear view schematic structural diagram of a fuel-rich gas conveying pipeline provided by an embodiment of the present invention;
FIG. 5 is a schematic cross-sectional view B-B of FIG. 4;
Fig. 6 is a schematic cross-sectional view of a turbine housing portion in an embodiment of the invention.
Reference numerals:
1, a turbine; 2 a turbine housing; 20 turbine passages; 200 gas outlet; 3, a gas generator; 30 gasifier elbow; 31 a nozzle; 4, a transmission shaft; 5, a turbine seat; 6 a first flange; 7 a second flange; 8 a fuel gas requiring part; 9 oxidant delivery pump.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings. The utility model discloses a particular embodiment is right the utility model discloses a protection does not play the limiting action. The protection scope of the present invention is subject to the claims.
It should be noted that, in the embodiment of the present invention, "front" and "rear" are explained in terms of the direction of conveying the rich fuel gas, and do not limit the protection scope of the present invention.
as shown in fig. 1-6, an embodiment of the present invention provides a rich fuel gas conveying pipeline, including a turbine 1, a turbine housing 2, a gas generator 3, and a turbine seat 5, where the turbine seat 5 is disposed at a front end of the turbine 1, and the turbine housing 2 is disposed at an interval around the turbine 1;
The turbine shell 2 is internally provided with an annular turbine channel 20, the gas generator 3 comprises a gas generator elbow 30, the gas generator 3 is connected with the turbine shell 2 through the gas generator elbow 30, a nozzle 31 is arranged at the joint of the gas generator elbow 30 and the turbine shell 2, and the nozzle 31 is arranged in a tangent mode with the turbine shell 7.
The annular turbine passage 14 is arranged to help the rich gas move along the direction of rotation of the turbine in the inner part so as to drive the turbine uniformly when flowing out of the gas outlet 19 in the next step, and the tangential arrangement of the nozzle 31 and the turbine shell 2 is arranged so as to reduce the loss of the gas flow speed of the rich gas in the flowing process and improve the efficiency of driving the turbine in the next step.
The inner surface of the turbine passage 20 is provided with a plurality of gas outlets 200 at the same angle, and the gas outlets 200 are communicated with the turbine passage 20 and the inside of the turbine shell 2.
The embodiment of the utility model provides an annular turbine passageway is designed in turbine shell, makes the gas collecting chamber of integration to be separated by 120 in turbine passageway 20 and design three gas export 200 and be convenient for the rich gas that comes from gas generator and evenly discharge drive turbine from three gas export 200, design three gas export 200 purpose around turbine passageway 20 and just be for solving the even drive turbine problem. Obviously, the utility model discloses do not restrict the quantity of gas export, can also set up to 5, 7. The utility model discloses do not restrict the quantity of gas export.
The embodiment of the utility model provides a fuel gas conveying pipeline is fired to richly for air turbine rocket engine provides the fuel gas that richly fires, can also provide the power source for the oxidizer delivery pump simultaneously.
Further, the fuel-rich gas conveying pipeline further comprises a fuel gas demand part 8, and the fuel gas demand part 8 is connected with the turbine shell 2 through the first flange 6.
The rich gas generated by the gas generator 3 is delivered through the gas generator elbow 30, then ejected into the turbine channel 20 through the nozzle 31, and then passed through the gas outlet 200 to the inside of the turbine to drive the turbine, and finally, the inside of the turbine is introduced into the gas demand section 8.
Further, a gas nozzle (not shown) is provided between the gas demand section 8 and the turbine casing 2.
Further, the turbine housing 2 and the turbine base 5 are connected through a second flange 7.
further, a transmission shaft 4 is connected to the turbine 1, the transmission shaft 4 extends to the outside of the turbine housing 2 through the turbine seat 5, and the other end of the transmission shaft 4 is connected to an oxidant delivery pump 9. When turbine 1 rotates, rotation may be transmitted to oxidant delivery pump 9 via drive shaft 4, thereby providing a source of power to the oxidant delivery pump.
the embodiment of the utility model provides a gas generator 3 drives turbine 1 through constantly providing rich gas and rotates. The embodiment of the utility model provides a turbine 1 rotates, can also drive oxidant delivery pump work through the transmission shaft. The utility model discloses gas generator 3 and turbine 1 not only can be used for carrying rich fuel gas, can also provide power for the oxidizer delivery pump.
Claims (5)
1. The fuel-rich gas conveying pipeline is characterized by comprising a turbine (1), a turbine shell (2), a gas generator (3) and a turbine seat (5), wherein the turbine seat (5) is arranged at the front end of the turbine (1), and the turbine shell (2) is arranged at the periphery of the turbine (1) at intervals;
An annular turbine channel (20) is arranged in the turbine shell (2), the gas generator (3) comprises a gas generator bent pipe (30), the gas generator (3) is connected with the turbine shell (2) through the gas generator bent pipe (30), a nozzle (31) is arranged at the connection position, and the nozzle (31) is arranged in a tangent mode with the turbine shell (7);
the inner surface of the turbine channel (20) is tangentially provided with a plurality of gas outlets (200), and the gas outlets (200) are communicated with the turbine channel (20) and the interior of the turbine shell (2).
2. the fuel-rich gas delivery line according to claim 1, further comprising a gas requirement (8), the gas requirement (8) being connected to the turbine housing (2) by a first flange (6).
3. the fuel-rich gas delivery duct according to claim 2, characterized in that a gas nozzle is provided between the gas demand (8) and the turbine casing (2).
4. The fuel-rich gas delivery duct according to claim 1, characterized in that the turbine housing (2) and the turbine seat (5) are connected by a second flange (7).
5. The fuel-rich gas delivery line according to claim 1, wherein a drive shaft (4) is further connected to the turbine (1), and the drive shaft (4) extends through the turbine seat (5) to the outside of the turbine housing (2) and is connected to the oxidant delivery pump (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920439730.XU CN209743063U (en) | 2019-04-03 | 2019-04-03 | Rich fuel gas conveying pipeline |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920439730.XU CN209743063U (en) | 2019-04-03 | 2019-04-03 | Rich fuel gas conveying pipeline |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209743063U true CN209743063U (en) | 2019-12-06 |
Family
ID=68719684
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920439730.XU Expired - Fee Related CN209743063U (en) | 2019-04-03 | 2019-04-03 | Rich fuel gas conveying pipeline |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209743063U (en) |
-
2019
- 2019-04-03 CN CN201920439730.XU patent/CN209743063U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191206 Termination date: 20200403 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |