CN116201615A - Water reaction metal fuel high-pressure turbine device with partial air inlet - Google Patents

Water reaction metal fuel high-pressure turbine device with partial air inlet Download PDF

Info

Publication number
CN116201615A
CN116201615A CN202211664420.0A CN202211664420A CN116201615A CN 116201615 A CN116201615 A CN 116201615A CN 202211664420 A CN202211664420 A CN 202211664420A CN 116201615 A CN116201615 A CN 116201615A
Authority
CN
China
Prior art keywords
gas
solid
phase flow
resistant cylinder
cylinder body
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202211664420.0A
Other languages
Chinese (zh)
Inventor
樊玮鹏
郝拥军
洪军伟
张赫
李红烨
张亚龙
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
China Shipbuilding Research Institute Seventh Research Institute Of China Shipbuilding Corp
Original Assignee
China Shipbuilding Research Institute Seventh Research Institute Of China Shipbuilding Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by China Shipbuilding Research Institute Seventh Research Institute Of China Shipbuilding Corp filed Critical China Shipbuilding Research Institute Seventh Research Institute Of China Shipbuilding Corp
Priority to CN202211664420.0A priority Critical patent/CN116201615A/en
Publication of CN116201615A publication Critical patent/CN116201615A/en
Pending legal-status Critical Current

Links

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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Architecture (AREA)
  • Hydraulic Turbines (AREA)

Abstract

The invention provides a partial-intake water-reaction metal fuel high-pressure turbine device, which comprises: the device comprises a supersonic Laval nozzle air inlet channel (1), a gas-solid two-phase flow abrasion resistant cylinder body (2), a water reaction metal fuel product outlet (3), a shaft hole (4) and a working device, wherein the supersonic Laval nozzle air inlet channel (1) is arranged on the gas-solid two-phase flow abrasion resistant cylinder body (2); the water reaction metal fuel product outlet (3) is arranged at the lower part of the gas-solid two-phase flow abrasion resistant cylinder body (2), and the shaft hole (4) is arranged on the side surface of the gas-solid two-phase flow abrasion resistant cylinder body (2); the acting device is arranged inside the gas-solid two-phase flow abrasion resistant cylinder body (2) and is connected with the shaft hole (4), so that energy loss is reduced, and propulsion efficiency is effectively improved.

Description

Water reaction metal fuel high-pressure turbine device with partial air inlet
Technical Field
The invention relates to the technical field of underwater vehicle power, in particular to a water reaction metal fuel high-pressure turbine device with partial air intake.
Background
With the continuous improvement of the voyage of submarines and surface ships in service in various countries, the continuous increase of the voyage speed and the great improvement of maneuverability, the torpedoes and other underwater weapons must have a great voyage speed to effectively kill enemy targets. The energy required for sailing an underwater vehicle is proportional to the cube of the speed, i.e. eight times the energy is required to double the speed of the vehicle. In order to increase the speed and range of an underwater vehicle, intensive research on the existing power system is required.
The power system of the underwater navigation body mainly comprises a thermal power system and an electric power system, and compared with the electric power system, the thermal power system has the advantages of high speed and long distance. Aiming at a thermodynamic system, the development of high-energy fuel and related power technologies has very important practical significance.
The water reaction metal fuel has very high energy characteristics, can greatly improve the specific power of the underwater vehicle, reduce the quality of a combustion chamber, improve the navigational speed of the underwater vehicle and increase the navigational range, is a research direction with bright prospect, and has more and more scientific and technological staff put into the research of the water reaction metal fuel. However, at present, the application of the water reaction metal fuel in the field of underwater power is mainly direct injection type propulsion, so that the energy loss is large, and the effective improvement of the propulsion efficiency is difficult to realize.
Disclosure of Invention
The invention provides a water reaction metal fuel high-pressure turbine device with partial air intake, which aims to solve the technical problems that in the prior art, the energy loss is large and the effective improvement of the propulsion efficiency is difficult to realize.
In order to solve the technical problems, the invention adopts the following technical scheme:
a partial-intake water-reactive metal-fuel high-pressure turbine apparatus comprising: the device comprises a supersonic Laval nozzle air inlet channel 1, a gas-solid two-phase flow wear resistant cylinder body 2, a water reaction metal fuel product outlet 3, a shaft hole 4 and a working device, wherein the gas-solid two-phase flow wear resistant cylinder body 2 is provided with the supersonic Laval nozzle air inlet channel 1; the water reaction metal fuel product outlet 3 is arranged at the lower part of the gas-solid two-phase flow abrasion resistant cylinder body 2, and the shaft hole 4 is arranged on the side surface of the gas-solid two-phase flow abrasion resistant cylinder body 2; the acting device is arranged inside the gas-solid two-phase flow abrasion resistant cylinder body 2 and is connected with the shaft hole 4.
Optionally, two supersonic Laval nozzle air inlets 1 are distributed on the side surface of the upper part of the gas-solid two-phase flow abrasion resistant cylinder body 2.
Optionally, the supersonic Laval nozzle air inlet channel 1 is connected with the gas-solid two-phase flow abrasion resistant cylinder body 2 in a bevelled mode.
Optionally, the supersonic Laval nozzle air inlet channel 1 and the gas-solid two-phase flow abrasion resistant cylinder body 2 are cast in an integrated molding mode.
Alternatively, the working device is fixed inside the gas-solid two-phase flow wear resistant cylinder 2 by means of a transmission shaft.
Alternatively, the working device comprises a high-speed wear-resistant impeller 5 and high-load impulse-type moving blades 6.
Optionally, the shaft hole 4 is formed in the center of the side surface of the gas-solid two-phase flow abrasion resistant cylinder 2.
Optionally, the water reaction metal fuel product outlet 3 is used as a working medium outlet.
Optionally, the supersonic Laval nozzle inlet 1 has a beveled borehole nozzle.
Alternatively, the gas-solid two-phase flow wear resistant cylinder 2 is the main structure of the device.
The beneficial effects of the invention are as follows: the invention provides a partial intake water reaction metal fuel high pressure turbine device, comprising: the device comprises a supersonic Laval nozzle air inlet channel 1, a gas-solid two-phase flow wear resistant cylinder body 2, a water reaction metal fuel product outlet 3, a shaft hole 4 and a working device, wherein the gas-solid two-phase flow wear resistant cylinder body 2 is provided with the supersonic Laval nozzle air inlet channel 1; the water reaction metal fuel product outlet 3 is arranged at the lower part of the gas-solid two-phase flow abrasion resistant cylinder body 2, and the shaft hole 4 is arranged on the side surface of the gas-solid two-phase flow abrasion resistant cylinder body 2; the acting device is arranged inside the gas-solid two-phase flow abrasion resistant cylinder body 2 and connected with the shaft hole 4, so that energy loss is reduced, and propulsion efficiency is effectively improved.
Drawings
FIG. 1 is an axial view of a partially admitted water reactive metal-fuel high pressure turbine assembly.
FIG. 2 is a top view of a partially admitted water reactive metal-fuel high pressure turbine apparatus.
FIG. 3 is an elevation view of a partially admitted water reactive metal-fuel high pressure turbine assembly.
FIG. 4 is a side view of a partially admitted water reactive metal-fuel high pressure turbine apparatus.
FIG. 5 is a cross-sectional view of a water reactive metal-fuel high pressure turbine apparatus A-A with partial intake.
FIG. 6 is a cross-sectional view of a water-reactive metal-fuel high-pressure turbine device B-B with partial intake.
FIG. 7 is an axial view of the supersonic Laval nozzle inlet.
FIG. 8 is a top view of an air inlet of the supersonic Laval nozzle.
FIG. 9 is an elevation view of an inlet of a supersonic Laval nozzle.
FIG. 10 is a side view of the supersonic Laval nozzle inlet.
Wherein, the 1-supersonic Laval nozzle air inlet channel, the 2-gas-solid two-phase flow abrasion resistant cylinder body, the 3-water reaction metal fuel product outlet, the 4-shaft hole, the 5-high rotation speed abrasion resistant impeller and the 6-high load impulse type moving blade are arranged in the same cylinder body
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is evident that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by a person skilled in the art without any inventive effort, are intended to be within the scope of the present invention, based on the embodiments of the present invention.
In order to solve the technical problems, the invention adopts the following technical scheme:
referring to fig. 1-10, an embodiment of the present invention provides a partial-intake water-reactive metal-fuel high-pressure turbine apparatus, comprising: the device comprises a supersonic Laval nozzle air inlet channel 1, a gas-solid two-phase flow wear resistant cylinder body 2, a water reaction metal fuel product outlet 3, a shaft hole 4 and a working device, wherein the gas-solid two-phase flow wear resistant cylinder body 2 is provided with the supersonic Laval nozzle air inlet channel 1; the water reaction metal fuel product outlet 3 is arranged at the lower part of the gas-solid two-phase flow abrasion resistant cylinder body 2, and the shaft hole 4 is arranged on the side surface of the gas-solid two-phase flow abrasion resistant cylinder body 2; the acting device is arranged inside the gas-solid two-phase flow abrasion resistant cylinder body 2 and is connected with the shaft hole 4.
Optionally, two supersonic Laval nozzle air inlets 1 are distributed on the side surface of the upper part of the gas-solid two-phase flow abrasion resistant cylinder body 2.
Optionally, the supersonic Laval nozzle air inlet channel 1 is connected with the gas-solid two-phase flow abrasion resistant cylinder body 2 in a bevelled mode.
Optionally, the supersonic Laval nozzle air inlet channel 1 and the gas-solid two-phase flow abrasion resistant cylinder body 2 are cast in an integrated molding mode.
Alternatively, the working device is fixed inside the gas-solid two-phase flow wear resistant cylinder 2 by means of a transmission shaft.
Alternatively, the working device comprises a high-speed wear-resistant impeller 5 and high-load impulse-type moving blades 6.
Optionally, the shaft hole 4 is formed in the center of the side surface of the gas-solid two-phase flow abrasion resistant cylinder 2.
Optionally, the water reaction metal fuel product outlet 3 is used as a working medium outlet.
Optionally, the supersonic Laval nozzle inlet 1 has a beveled borehole nozzle.
Alternatively, the gas-solid two-phase flow wear resistant cylinder 2 is the main structure of the device.
The working principle of the device of the invention is as follows:
the high-temperature high-pressure water reaction metal fuel gas-solid two-phase flow combustion products expand twice through the contraction section and the expansion section of the supersonic Laval nozzle air inlet channel 1, and the pressure reduction and acceleration reach supersonic speed and enter into the impulse type moving blade 6 flow channel. The supersonic gas-solid two-phase flow pushes the impulse moving blade 6 to convert the available enthalpy and kinetic energy into kinetic energy of the impulse moving blade 6 and the high-rotation-speed wear-resistant impeller 5, and the high-rotation-speed wear-resistant impeller 5 rotates at a high speed and then transmits the rotation speed to the rotating shaft equally through the shaft hole 4, so as to output shaft work. After the supersonic gas-solid two-phase flow does work, the supersonic gas-solid two-phase flow further expands in the gas-solid two-phase flow abrasion resistant cylinder body 2 and is discharged out of the turbine through the water reaction metal fuel product outlet 3.
The device adopts the inclined drilling spray pipe, the airflow channel is not folded in the moving direction, and the flow separation is generally avoided; meanwhile, the drilling spray pipe has smaller friction area and no edge angle, and can achieve high dimensional accuracy and surface roughness.
The device adopts water to react metal fuel, has high energy density and low mass flow, and has high airflow speed flowing out of the section of the outlet of the air inlet channel, so that the airflow speed entering the movable vane flow channel is high, the outlet area of the air inlet channel and the inlet area of the corresponding movable vane flow channel are small, the workability of the outlet diameter of the air inlet channel and the height of the blade is ensured by adopting a local air inlet mode, and meanwhile, the energy loss is reduced, and the efficiency and the power of the turbine are increased.
In an application scene, the device is designed to have the rotating speed of 55000r/min, the local air inlet rate of 0.22, the reaction force of 0.03, the ratio of the absolute air inlet speed to the peripheral speed of an impeller of 0.4634, the expansion angle of a Laval nozzle of 8 degrees, the absolute air flow angle of a movable vane outlet of 89.6216 degrees, the air flow direction of the movable vane of the device of the invention is axial, and the corresponding residual speed loss is small.
The embodiment of the invention has the following beneficial effects:
the water reaction metal fuel high-pressure turbine device provided by the embodiment of the invention breaks through the limit of traditional direct injection propulsion, and can efficiently convert the energy carried by the water reaction metal fuel high-temperature high-pressure gas-solid two-phase combustion products into shaft work and output the shaft work to the propulsion device, so that the high-speed long-endurance navigation with the propulsion power of not less than 400KW of the underwater vehicle is realized.
According to the embodiment of the invention, a novel turbine device composition form of combining the supersonic Rafael drilling spray pipe and the high-load impulse moving blade is adopted, and a local air inlet mode is adopted, so that high-temperature high-pressure gas-solid two-phase products generated by combustion of the water reaction metal fuel are fully utilized in the flow of the spray pipe and the work of the blade, the overall work efficiency of the system is greatly improved, and the endurance time is effectively prolonged.
The high-pressure turbine device provided by the embodiment of the invention consumes great enthalpy drop in a single stage, at the moment, the pressure ratio of the inlet and the outlet of the spray pipe is far smaller than the critical pressure ratio, the airflow at the outlet of the spray pipe reaches supersonic speed, and the Laval bevel drilling spray pipe is used, so that the motion direction of the airflow is not turned over, and the flow separation is avoided; the drilling spray pipe has smaller friction area, no edge angle and can achieve high dimensional accuracy and surface roughness
The energy density of the water reaction metal fuel is extremely high, the gas flow required by underwater navigation is less than that of the traditional energy source, the gas flow flowing out of the section of the nozzle outlet is high, and the gas flow entering the movable vane runner is high, so that the area of the nozzle outlet and the area of the corresponding movable vane runner inlet are small, the design difficulty is increased, and simultaneously, the larger energy loss is also caused. The invention adopts a local air inlet mode to reduce the design difficulty of the diameter of the outlet of the spray pipe and the height of the blades and improve the efficiency and the power of the turbine.
The local air-intake water-reaction metal fuel high-pressure turbine device mainly comprises a drilling spray pipe, a movable blade grid rotor and an impeller, is connected by adopting a specially designed annular body, is reasonably arranged in space arrangement, realizes the optimized design of small space, high load and high efficiency, can meet the long endurance requirement under high-power sailing, and can greatly improve the fight performance of an underwater high-efficiency striking weapon system.
In the description of the present specification, a particular feature, structure, material, or characteristic may be combined in any suitable manner in one or more embodiments or examples.
Of course, the present invention is capable of other various embodiments and its several details are capable of modification and variation in light of the present invention by one skilled in the art without departing from the spirit and scope of the invention as defined in the appended claims.

Claims (10)

1. A partially-intake water-reactive metal-fuel high-pressure turbine apparatus, comprising: the device comprises a supersonic Laval nozzle air inlet channel (1), a gas-solid two-phase flow abrasion resistant cylinder body (2), a water reaction metal fuel product outlet (3), a shaft hole (4) and a working device, wherein the supersonic Laval nozzle air inlet channel (1) is arranged on the gas-solid two-phase flow abrasion resistant cylinder body (2); the water reaction metal fuel product outlet (3) is arranged at the lower part of the gas-solid two-phase flow abrasion resistant cylinder body (2), and the shaft hole (4) is arranged on the side surface of the gas-solid two-phase flow abrasion resistant cylinder body (2); the acting device is arranged inside the gas-solid two-phase flow abrasion resistant cylinder body (2) and is connected with the shaft hole (4).
2. The device according to claim 1, characterized in that two supersonic rahal jet air inlets (1) are distributed on the upper side of the gas-solid two-phase flow wear resistant cylinder (2).
3. The device according to claim 2, characterized in that the supersonic raval nozzle inlet (1) is connected with the gas-solid two-phase flow wear resistant cylinder (2) in a chamfer form.
4. A device according to claim 3, characterized in that the supersonic raval nozzle inlet (1) is cast in one piece with the gas-solid two-phase flow wear resistant cylinder (2).
5. The device according to claim 4, characterized in that the working device is fixed inside the gas-solid two-phase flow wear resistant cylinder (2) by means of a transmission shaft.
6. The device according to claim 5, characterized in that the working means comprise high-speed wear-resistant impellers (5), high-load impulse rotor blades (6).
7. The device according to claim 6, characterized in that the shaft hole (4) is provided in the lateral centre of the gas-solid two-phase flow wear resistant cylinder (2).
8. The device according to claim 7, characterized in that the water-reactive metal fuel product outlet (3) serves as a working medium outlet.
9. The device according to claim 8, characterized in that the supersonic raval nozzle inlet (1) has a chamfer drilling nozzle.
10. The device according to claim 9, characterized in that the gas-solid two-phase flow wear resistant cylinder (2) is the main structure of the device.
CN202211664420.0A 2022-12-23 2022-12-23 Water reaction metal fuel high-pressure turbine device with partial air inlet Pending CN116201615A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211664420.0A CN116201615A (en) 2022-12-23 2022-12-23 Water reaction metal fuel high-pressure turbine device with partial air inlet

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211664420.0A CN116201615A (en) 2022-12-23 2022-12-23 Water reaction metal fuel high-pressure turbine device with partial air inlet

Publications (1)

Publication Number Publication Date
CN116201615A true CN116201615A (en) 2023-06-02

Family

ID=86518290

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211664420.0A Pending CN116201615A (en) 2022-12-23 2022-12-23 Water reaction metal fuel high-pressure turbine device with partial air inlet

Country Status (1)

Country Link
CN (1) CN116201615A (en)

Similar Documents

Publication Publication Date Title
US6138456A (en) Pressure exchanging ejector and methods of use
US7497666B2 (en) Pressure exchange ejector
CN103380051A (en) Device for reducing resistance of ship body
KR101599681B1 (en) Hull resistance reduction system and hull resistance reduction method
CN102536511A (en) High thrust aircraft engine
CN110107426A (en) Across the medium flight device power device shared based on combustion chamber between grade and turbine water sky
CN203906118U (en) Gas cooling system for turbine-based combined-cycle engine
CN102114908A (en) Pump-jet water propeller system for five-element combined ship
CN102530217B (en) Fast and efficient water spray propelling technology
CN102588112A (en) Jet-flow efficient thermal power system
CN203906120U (en) Combined engine for unmanned combat aircraft
CN202611925U (en) Engine of high-thrust aircraft
US4424042A (en) Propulsion system for an underwater vehicle
CN115306584A (en) Liquid rocket engine turbopump containing contra-rotating turbine
US3396538A (en) Water injection for thrust augmentation
CN203906119U (en) Turbine-based combined cycle engine of wide flight envelope aircraft
CN116201615A (en) Water reaction metal fuel high-pressure turbine device with partial air inlet
US20020095935A1 (en) Single shaft hybrid supercharger system
CN115853677A (en) Turbine exhaust gas exhaust structure of liquid rocket engine
JP2010071273A (en) Low isothermal compression gas turbine engine
RU2303152C1 (en) Jet engine installation of flight vehicle
WO2006069480A1 (en) Rotary engine
CN203847273U (en) Fan system for turbine-based combined cycle engine
CN202900416U (en) Jet-flow high-efficiency thermal power system
KR102329602B1 (en) Vessel Operating System And Its Operating Device Using Liquid Air

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination