CN115095396A - Turbine outlet diversion elbow structure of liquid rocket engine - Google Patents
Turbine outlet diversion elbow structure of liquid rocket engine Download PDFInfo
- Publication number
- CN115095396A CN115095396A CN202210729663.1A CN202210729663A CN115095396A CN 115095396 A CN115095396 A CN 115095396A CN 202210729663 A CN202210729663 A CN 202210729663A CN 115095396 A CN115095396 A CN 115095396A
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- flow
- turbine
- rocket engine
- liquid rocket
- bent pipe
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- 239000007788 liquid Substances 0.000 title claims abstract description 19
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 8
- 230000009471 action Effects 0.000 claims abstract description 4
- 230000007704 transition Effects 0.000 claims description 19
- 210000001503 joint Anatomy 0.000 claims description 7
- 230000008859 change Effects 0.000 claims description 5
- 239000000411 inducer Substances 0.000 claims 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims 1
- 239000007789 gas Substances 0.000 description 11
- 230000008602 contraction Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
- F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A liquid rocket engine turbine outlet diversion elbow structure belongs to the technical field of machinery. The invention comprises a rectification cascade 1, a bent pipe 2, an outlet flange 3, a flow guide cover 4 and a flow guide cone 5. Wherein, an outer ring flange of the rectifying blade cascade is connected with an upstream turbine shell, and an outlet flange is connected with a downstream gas elbow. High-temperature and high-pressure gas generated by the precombustion chamber passes through the turbine rotor to do work, enters the rectification cascade passage from the turbine shell, obviously weakens the rotational flow under the action of the guide vanes, then enters the outlet flange along the passage formed by the guide cover and the bent pipe, and finally is guided to the downstream gas bent pipe and the thrust chamber through the outlet flange. The turbine outlet diversion elbow structure can efficiently divert the gas at the turbine outlet to a downstream thrust chamber, and can reliably connect the structure of the turbine pump shell and the thrust chamber, thereby achieving the diversion function and serving as a bearing structure.
Description
Technical Field
The invention relates to a liquid rocket engine turbine outlet diversion elbow structure, and belongs to the technical field of machinery.
Background
In liquid rocket engines, a turbo pump is used as a core component of a propellant supply system, and the performance and the structure of the turbo pump are directly related to the performance and the reliability of the engine. For engines requiring high thrust-to-weight ratios, the power-to-weight ratio of the turbopump is high, which requires that the components of the turbopump be reduced in size and weight as much as possible while meeting performance requirements.
In the afterburning cycle engine, the outlet pipe of the turbine is used for guiding high-temperature and high-pressure gas generated by the precombustion chamber and used for pushing the turbine to do work into the head part of the thrust chamber on one hand; on the other hand, the turbine pump is also used as a force bearing structural part and connects the whole turbine pump with the thrust chamber. Therefore, when the turbine outlet pipe works in a complex stress environment such as high temperature, high pressure and vibration, the structural failure of the turbine outlet pipe can cause structural damage and functional loss of the engine.
In the prior art, a flow guide structure is not arranged in a turbine outlet pipe, so that the mixing of main flow and secondary flow in a bent pipe, the gas swirl at a rotor outlet and the like can cause the increase of flow loss, thereby causing the reduction of work capacity of a turbine. In addition, the existing scheme generally adopts a bent pipe structure with equal wall thickness, the strength allowance of the inner side of the bent pipe is large, the strength allowance of the outer side of the bent pipe is small, the bent pipe has larger weight under the condition of meeting the strength requirement, and the design requirement of high thrust-weight ratio of an engine is not met.
Disclosure of Invention
The invention solves the technical problems that: the defects of the prior art are overcome, the diversion elbow structure at the turbine outlet of the liquid rocket engine is provided, and the technical problems that the work capacity of the turbine is insufficient due to large flow loss in the elbow, and the thrust-weight ratio of the engine is reduced due to large size and weight of the elbow structure are solved.
The technical solution of the invention is as follows: a turbine outlet diversion elbow structure of a liquid rocket engine comprises a rectification cascade, a diversion cover, a diversion cone, an elbow and an outlet flange;
the gas channel is formed by the rectifying blade cascade, the bent pipe and the outlet flange, the front end of the rectifying blade cascade is connected with the flow guide cover, the outer ring flange of the rectifying blade cascade is connected with the upstream turbine shell, and the outlet flange is connected with the downstream gas bent pipe;
the front end of the guide cover is connected with a guide cone, and a closed cavity is formed inside the guide cone;
high-temperature and high-pressure gas generated by the precombustion chamber does work through the turbine rotor, enters the rectification cascade channels from the turbine shell, obviously weakens the rotational flow under the action of the guide vanes, then enters the outlet flange along the channel formed by the guide cover and the bent pipe, and finally is guided to the downstream gas bent pipe and the thrust chamber through the outlet flange.
Furthermore, the rectifying blade cascade comprises an outer ring, an inner ring and a plurality of guide blades;
the outer ring is of a flange structure and is used for being connected with an upstream turbine shell, and the butt joint part of the outer ring and the bent pipe adopts two semi-rings with different wall thicknesses;
the guide vanes are straight vanes adopting symmetrical vane profiles;
the inner ring is of a symmetrical taper pipe structure with equal wall thickness, and the taper pipe is adopted to facilitate smooth transition of the inner ring and the air guide sleeve.
Further, the number of the guide vanes is 12, the radius of the front edge of each vane can be selected to be 2 times of that of the tail edge, and the included angle of the profiles of the outlet sections of the vanes can be selected to be 12 degrees.
Furthermore, the included angle between the conical surface of the inner ring and the central axis is 15 degrees.
Furthermore, the bent pipe and the flow guide cover are both of a contraction type circular pipe structure, and the center lines of the circular pipes are overlapped, so that the flow cross section area of the fuel gas is unchanged along the flow direction.
Furthermore, the center line of the elbow is tangent to the center lines of the upper rectifying blade cascade and the outlet flange, so that the curvature change of the streamline of the channel is continuous.
Furthermore, the inner side of the bent pipe has large curvature, and the outer side of the bent pipe has small curvature.
Further, the elbow comprises two half rings with different thicknesses, and the two half rings are smoothly transited at the thickness transition position.
Furthermore, the cross section of the flow guide cover is equal in thickness, and the head part of the flow guide cone is closed, so that the inner ring of the flow guide cascade, the flow guide cover and the flow guide cone form an inner closed cavity, and the vortex flow of the cavity of the turbine rotor disk is separated from the main flow of the rotor blade channel.
Further, the top taper angle of the guide cone is selected to be 60 degrees.
Compared with the prior art, the invention has the advantages that:
(1) according to the invention, the combination structure of the blade grid and the flow guide cone is arranged in the turbine outlet elbow, so that the obvious effects of inhibiting the mixing of the internal rotational flow and the secondary flow of the outlet elbow and reducing the flow loss are achieved;
(2) the invention obtains the remarkable effects of reducing the weight of the outlet pipe of the turbine and improving the stress state of the elbow by designing the equal-strength elbow structure with unequal wall thickness and smooth transition;
(3) the invention realizes a turbine outlet flow guiding elbow structure with good flow guiding performance, compact structure and light weight by comprehensively applying the flow guiding structure and the elbow structure with different wall thicknesses, and achieves the remarkable effect of taking high performance and structural reliability into consideration.
Drawings
FIG. 1 shows a turbine outlet flow guiding elbow structure of a liquid rocket engine, which comprises a flow guiding cascade 1, an elbow 2, an outlet flange 3, a flow guiding cover 4 and a flow guiding cone 5.
FIG. 2 is a schematic view of a vane profile of a guide vane, where L is a vane length dimension, S is a vane thickness dimension, 2R is a vane leading edge radius, and R is a vane trailing edge radius.
FIG. 3 is a schematic cross-sectional view of the elbow, where Φ is the inner diameter of the elbow, δ 1 is the thickness dimension of the inner half ring of the elbow, δ 2 is the thickness dimension of the outer half ring of the elbow, D1 is the profile dimension of the transition position of the inner and outer half rings, and R is the dimension of the rounding of the smooth transition.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The following describes in further detail a turbine outlet flow-guiding elbow structure of a liquid rocket engine provided in an embodiment of the present application with reference to the drawings of the specification, and specific implementation manners may include (as shown in fig. 1 to 3): the flow guide device comprises a flow guide blade cascade, a flow guide cover, a flow guide cone, a bent pipe and an outlet flange; wherein the rectification cascade, the elbow pipe and the outlet flange form a fuel gas channel, the front end of the rectification cascade is connected with the flow guide cover, the front end of the flow guide cover is connected with a flow guide cone, and a closed cavity is formed inside the flow guide cone;
the bent pipe is of a shrinkage round pipe structure, the center line of the round pipe is an arc, the bent pipe is composed of an inner half pipe and an outer half pipe, the thickness of the inner half pipe is large, the thickness of the outer half pipe is small, and the inner half pipe is in smooth transition at the butt joint position of the inner half pipe and the outer half pipe; the butt joint part of the outlet flange and the elbow pipe is composed of two semi-rings with unequal wall thicknesses, and smooth transition is realized at the butt joint position;
the rectifying blade cascade consists of an inner ring, an outer ring and a plurality of circumferentially and uniformly distributed guide vanes; the connecting part of the outer ring and the upstream turbine shell is of a flange structure, the connecting part of the outer ring and the elbow is composed of two half rings with different wall thicknesses, and smooth transition is realized at the butt joint position; wherein the inner ring is a taper pipe structure with equal wall thickness and taper of 15 degrees; wherein the guide vane is a straight vane with symmetrical vane profile;
the air guide sleeve is of a contraction type circular tube structure with equal wall thickness, and the center line of the circular tube is superposed with the center line of the bent tube; the head part of the guide cone is closed, and the cone angle is 60 degrees.
In the solution provided by the embodiment of the present application, as shown in fig. 1, the flow guide device includes a flow guide cascade 1, an elbow 2, an outlet flange 3, a flow guide cover 4, and a flow guide cone 5. Wherein, an outer ring flange of the rectifying blade cascade is connected with an upstream turbine shell, and an outlet flange is connected with a downstream gas elbow. High-temperature and high-pressure gas generated by the precombustion chamber does work through the turbine rotor, enters the rectification cascade channels from the turbine shell, obviously weakens the rotational flow under the action of the guide vanes, then enters the outlet flange along the channel formed by the guide cover and the bent pipe, and finally is guided to the downstream gas bent pipe and the thrust chamber through the outlet flange. The turbine outlet diversion elbow structure can efficiently divert the gas at the turbine outlet to a downstream thrust chamber, and can reliably connect the structure of the turbine pump shell and the thrust chamber, thereby achieving the diversion function and serving as a bearing structure.
The rectification cascade 1 is composed of an outer ring, an inner ring and a plurality of guide vanes, wherein the outer ring is of a flange structure and is convenient to be connected with an upstream turbine shell, and the butt joint part of the outer ring and a bent pipe is composed of two semi-rings with unequal wall thicknesses, so that smooth transition of the connection position is ensured, and local stress concentration is avoided. The guide vane is a straight vane with symmetrical vane profile, and the vane profile is shown in figure 2. The symmetrical blade profiles are adopted, the radius of the front edge of each blade is large, and airflow in different rotational flow directions can be guided to the axial direction, so that the rotational flow direction change of the rotor outlet under different working conditions is adapted. Preferably, the number of the guide vanes can be 12, the radius of the front edge of each vane can be 2 times of that of the tail edge of each vane, and the included angle of the profiles of the outlet sections of the vanes can be 12 degrees. The inner ring of the rectification cascade 1 is of a symmetrical taper pipe structure with equal wall thickness, and the taper pipe is adopted to facilitate smooth transition of the inner ring and the air guide sleeve, so that great curvature change at the transition position is avoided. Preferably, the angle between the conical surface and the central axis is chosen to be 15 °.
The bent pipe 2 and the flow guide cover 4 both adopt a contraction type round pipe structure, and the central lines of the round pipes are overlapped, so that the flow cross section area of the fuel gas is basically unchanged along the flow direction, and the stability of gas flow parameters is kept and the flow loss is reduced. The central line of the elbow is tangent to the central lines of the upper rectifying blade cascade and the outlet flange, so that the change of the streamline curvature of the channel is continuous. The bent pipe has large inner curvature, small outer curvature, large inner stress and small outer stress under the condition of the same thickness. In order to reduce the weight of the elbow pipe on the premise of meeting the strength requirement, according to the equal strength design principle, the elbow pipe consists of two semi-rings with unequal thicknesses, the cross section of the elbow pipe is shown as the attached drawing 3, and the transition is smooth at the thickness transition position. Preferably, the rounded transition is used at the thickness transition point by first flattening the inner ring on one side with the outer diameter dimension D1 of the outer ring, and then flattening the transition point. The bend 2 has a comparable strength margin and a weight reduction of about 1/3 compared to a constant thickness bend.
The inside and the outside of the air guide sleeve 4 basically have no pressure difference, and the stress is very small, so that the air guide sleeve is designed into a section with equal thickness. The head of the guide cone is closed, so that an inner closed cavity is formed by the inner ring of the rectifying cascade, the guide cover and the guide cone, the vortex flow of the rotor disc cavity of the turbine is separated from the main flow of the rotor blade channel, the disturbance of the vortex flow of the disc cavity on the main flow is avoided, and the uniformity of main flow parameters is improved. Preferably, the cone angle of the top of the guide cone is selected to be 60 °.
Preferably, the rectifying cascade 1, the elbow 2, the outlet flange 3, the air guide sleeve 4 and the air guide cone 5 are connected by welding.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. The utility model provides a liquid rocket engine turbine export water conservancy diversion return bend structure which characterized in that: the device comprises a rectification cascade, a flow guide cover, a flow guide cone, a bent pipe and an outlet flange;
the gas channel is formed by the rectifying blade cascade, the bent pipe and the outlet flange, the front end of the rectifying blade cascade is connected with the flow guide cover, the outer ring flange of the rectifying blade cascade is connected with the upstream turbine shell, and the outlet flange is connected with the downstream gas bent pipe;
the front end of the guide cover is connected with a guide cone, and a closed cavity is formed inside the guide cone;
high-temperature and high-pressure gas generated by the precombustion chamber does work through the turbine rotor, enters the rectification cascade channels from the turbine shell, obviously weakens the rotational flow under the action of the guide vanes, then enters the outlet flange along the channel formed by the guide cover and the bent pipe, and finally is guided to the downstream gas bent pipe and the thrust chamber through the outlet flange.
2. The liquid rocket engine turbine exit inducer bend structure of claim 1, wherein: the rectifying blade cascade comprises an outer ring, an inner ring and a plurality of guide vanes;
the outer ring is of a flange structure and is used for being connected with an upstream turbine shell, and two half rings with different wall thicknesses are adopted at the butt joint part of the outer ring and the elbow;
the guide vanes are straight vanes adopting symmetrical vane profiles;
the inner ring is of a symmetrical taper pipe structure with equal wall thickness, and the taper pipe is adopted to facilitate smooth transition of the inner ring and the air guide sleeve.
3. The liquid rocket engine turbine exit nozzle elbow structure of claim 2, wherein: the number of the guide vanes is 12, the radius of the front edge of each vane can be 2 times of that of the tail edge, and the included angle of the molded surface of the outlet section of each vane can be 12 degrees.
4. The liquid rocket engine turbine exit inducer bend structure of claim 2, wherein: the included angle between the conical surface of the inner ring and the central axis is 15 degrees.
5. The liquid rocket engine turbine exit inducer bend structure of claim 1, wherein: the bent pipe and the flow guide cover are both of shrinkage circular pipe structures, and the center lines of the circular pipes are overlapped, so that the flow direction of the gas through-flow sectional area is unchanged.
6. The liquid rocket engine turbine exit nozzle elbow structure of claim 1, wherein: the central line of the elbow is tangent to the central lines of the upper rectifying blade cascade and the outlet flange, so that the change of the streamline curvature of the channel is continuous.
7. The liquid rocket engine turbine exit inducer bend structure of claim 1, wherein: the inner side curvature of the bent pipe is large, and the outer side curvature is small.
8. The liquid rocket engine turbine exit inducer bend structure of claim 1, wherein: the elbow comprises two semi-rings with different thicknesses, and the thickness transition positions are in smooth transition.
9. The liquid rocket engine turbine exit nozzle elbow structure of claim 1, wherein: the cross section of the flow guide cover is equal in thickness, the head of the flow guide cone is closed, so that the inner ring of the flow guide cascade, the flow guide cover and the flow guide cone form an inner closed cavity, and the vortex flow of the cavity of the turbine rotor disk is separated from the main flow of the rotor blade channel.
10. The liquid rocket engine turbine exit nozzle elbow structure of claim 9, wherein: the top taper angle of the flow guide cone is 60 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210729663.1A CN115095396A (en) | 2022-06-24 | 2022-06-24 | Turbine outlet diversion elbow structure of liquid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210729663.1A CN115095396A (en) | 2022-06-24 | 2022-06-24 | Turbine outlet diversion elbow structure of liquid rocket engine |
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| CN115095396A true CN115095396A (en) | 2022-09-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210729663.1A Pending CN115095396A (en) | 2022-06-24 | 2022-06-24 | Turbine outlet diversion elbow structure of liquid rocket engine |
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