阅读说明：本技术 超音速超高压二氧化碳压缩机机组 (Supersonic speed super-pressure carbon-dioxide gas compressor unit ) 是由 何备荒 魏宗胜 魏绍峻 宋赞 罗幼如 罗志 于 2019-08-23 设计创作，主要内容包括：本发明公开了一种超音速超高压二氧化碳压缩机机组,属于激波压缩领域。本发明针对现有技术存在的三项技术难题,主要解决两级压缩出口压力不能达到50MPa的缺陷,并在此基础上进一步解决超高压级起动期间用回流到压缩机进口,造成的能量浪费以及超高压力、超高转速转子的轴向力平衡和轴承型式。本发明采用三级超音速激波压缩,两组第二级向一组第三级供气,压缩机起动期间无需回流。因超音速压缩单级压比大,第一级和第二级的排气温度很高,设置換热器,避免后一级进气中的音速增高,不能产生激波的问题。本发明可促进低成本、超高压二氧化碳压缩机在《碳捕集与封存》和《提高原油采收率》的工业化应用。(The invention discloses a kind of supersonic speed super-pressure carbon-dioxide gas compressor units, belong to shock wave compression field.The present invention is directed to three technology problem of the existing technology, the defect of 50MPa cannot be reached by mainly solving two stages of compression outlet pressure, and further solve superelevation on this basis and arbitrarily downgrade during starting with flowing back into compressor inlet, caused by energy dissipation and hyperpressure, the axial force balance of ultrahigh rotating speed rotor and bearing type.The present invention uses three-level supersonic speed shock wave compression, and two groups of second level are supplied to one group of third level, without reflux during compressor start.Because supersonic compression single-stage pressure ratio is big, the delivery temperature of the first order and the second level is very high, and heat exchanger is arranged, avoids the velocity of sound in rear stage air inlet from increasing, cannot lead to the problem of shock wave.The present invention can promote low cost, super-pressure carbon-dioxide gas compressor " carbon capture with seal up for safekeeping " and " raising oil recovery factor " industrial applications.)

1. supersonic speed super-pressure carbon-dioxide gas compressor unit, including inlet casing, pre- propeller runner, entry guide vane, rotor, exhaust Casing, step-up gear, shaft coupling and motor, it is characterised in that: three-level supersonic speed shock wave compression is used, by sub-high pressure first The third level shock wave compression component composition of grade shock wave compression component, the second level shock wave compression component of high pressure and super-pressure, institute The first order shock wave compression component of sub-high pressure is stated by being arranged symmetrically in two groups of sub-high pressure shock wave compressions of the first pinion shaft end Unit composition and parallel running, the second level shock wave compression component of the high pressure is by being arranged symmetrically in the second pinion shaft end Two groups of high pressure shock wave compression unit compositions and parallel running, the third level shock wave compression component of the super-pressure is by being arranged in third Pinion shaft is formed far from one group of super-pressure shock wave compression unit of motor side corresponding end.

2. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 1, it is characterised in that: the sub-high pressure First order shock wave compression component and high pressure second level shock wave compression component between and high pressure second level shock wave compression group Gas heat exchanger is provided between part and the third level shock wave compression component of super-pressure.

3. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 1, it is characterised in that: the sub-high pressure First order shock wave compression component and high pressure second level shock wave compression component air intake duct contraction section compression ramp before machine Setting bypass air extractor, flows back into compressor inlet for compressed portion gas during compressor start on shell, establishes Supersonic speed shock wave is closed return valve by bypass reflux control system after oblique shock wave system stablizes, when normal operation Without reflux；And the third level is one group of super-pressure shock wave compression unit, is supplied from two groups of second level high pressure shock wave compression units to it Gas is not provided with bypass air extractor on casing.

4. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 1, it is characterised in that: three grades swash Wave compression assembly corresponds to the rotor in shock wave compression unit and connects respectively with corresponding pinion shaft end, the shock wave of three grades The steering of the corresponding rotor of the airflow direction of compression assembly is opposite.

5. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 1, it is characterised in that: three grades swash Wave compression assembly corresponds to together with inlet casing, rotor casing in shock wave compression unit be bolted with body, then fixes Onto the outer wall of step-up gear.

6. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 1, it is characterised in that: entire supersonic speed Super-pressure carbon-dioxide gas compressor unit uses a motor, a step-up gear and a set of diaphragm coupling.

7. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 1, it is characterised in that: the sub-high pressure First order shock wave compression component and the second level shock wave compression component of high pressure to be all made of two rotors being arranged symmetrically in parallel, and The back-to-back both ends for being mounted on corresponding pinion shaft, the rotor installation of the third level shock wave compression component of the super-pressure In the end of corresponding pinion shaft, five rotors are axial admission.

8. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 1, it is characterised in that: the three-level swashs In wave compression assembly, the root diameter in shock wave compression component from the first order to the third level gradually successively decreases and revolving speed is incremented by, In Pinion gear is respectively arranged on pinion shaft in three-level shock wave compression component, three in the three-level shock wave compression component are small Gear is engaged with the gear wheel in step-up gear respectively, drives three pinion gears simultaneously by a gear wheel.

9. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 8, it is characterised in that: the gear wheel It is non-integer with the gear ratios of pinion gears at different levels, the number of teeth of each pair of meshing gear prime number each other.

10. supersonic speed super-pressure carbon-dioxide gas compressor unit according to claim 8, it is characterised in that: described big Gear is nearby provided with bidirectional propulsion disk with the pitch circle that corresponding pinion gear relative velocity is zero, is provided with six on three pinion shafts There are 2 °~3 ° of small gradient in a thrust disc, the side of the thrust disc.

Technical field

Wataru and supersonic compressor of the present invention, and in particular to a kind of super-pressure pressurized carbon dioxide using shock wave compression technology Contracting machine.

Background technique

The energy characteristic of China is based on coal, and the year total emission volumn of carbon dioxide gas has occupied second place of the world, it is necessary to The step of Expedite the application " carbon capture with seal up for safekeeping " technology (abbreviation CCS technology Carbon dioxide Capture and Storage) It cuts down, to realize the substantially emission reduction of greenhouse gases.Clean air is natural environment for the survival of mankind.

China Petroleum external dependence degree in 2017 rises to 67.4%, the economy of Oil Safety issue concerns to China, military affairs Safety.Countermeasure first is that " improve oil recovery factor " technology (abbreviation EOR technology Enhanced Oil Recovery), China Current EOR technology mainly uses multistage centrifugal series connection of pumps injection high pressure or the high-pressure water displacement of reservoir oil.Since China is faced with more and more Severe water problems, many oil fields are distributed in the desert area of water shortage, the H of displacement of reservoir oil by filling water again₂O-EOR technology is restricted.

U.S.'s last century the eighties have begun to " CO₂The research and industrial applications of-EOR ".With oilfield exploitation It carries out, reservoir pressure is constantly reducing, for being normally carried out for production of recovering the oil, it is necessary to maintain the pressure of oil reservoir.U.S.'s last century Before the fifties, high pressure water is perfused to the earth's crust with high pressure water-injection pump, strata pressure is kept, with the high pressure water drive oil of 20~40MPa. The U.S. becomes the important method for improving recovery ratio with carbon dioxide drive later.According to " Gerald L.Boner, David CO in P.Gall, EOR application₂Compression [J] Oilfields engineering, 2003, (6), 5-6 ", injection 27.6 in oil reservoir~ 41.4MPa CO₂After being dissolved in oil, make crude oil volume expansion, viscosity reduces, and oil water interfacial tension reduces, and considerably increases oil recovery Speed.But big-flow high-pressure CO₂Reciprocating compressor, expensive, occupied space is big, and wet carbon dioxide gas contains H again₂S has corrosion Property, compressor service life are not grown.Existing centrifugal CO₂Compressor delivery pressure highest 15MPa, polytropic efficiency is low, is not able to satisfy “CO₂- EOR " project is to 50MPa super-pressure CO₂The demand of compressor.

The beginning of this century, small-sized high-tech company Ramgen company, one, the U.S. use for reference supersonic fighterplane air intake duct shock wave pressure " supersonic compressor " of the principle invention of contracting air, breaches the air inlet Mach Number Never To Be Exceeded of current centrifugal compressor theory provision (the ratio between gas velocity and velocity of sound) must not exceed 0.90 basic norm, and the relative Mach number of air inlet is increased to 2 or so instead, utilize Shock wave carrys out compressed gas, and single-stage pressure ratio increases severely from 1.6~1.8 to 10, and the series of same pressure differential compressor is kept to two-stage from 12 grades, Compression efficiency increases, the big drop of manufacturing cost.This is such as to be used for CO to the theoretical subversive innovation of conventional centrifugal compressor₂ Gas compression can meet " carbon capture and seal up for safekeeping " and " raising oil recovery factor " project to high pressure ratio, low cost CO₂Gas compression The urgent need of machine.

In order to capture Chinese market, Ramgen company and the first backward China of General Electric Company have applied a collection of related The patent of supersonic compressor.This brand-new technology for the ease of accurate understanding will be dispersed on beauty, middle patent and technical data Essence, sort out " core element of shock wave compression " below.

See 1 rotor schematic diagram of this specification attached drawing (Fig. 6 of Ramgen company US 7,334 " supersonic compressor " patent) With 2 rotor gas flow of attached drawing and (La Mu King Company CN 101,918,719B " the starting supersonic compression of bypass reflux schematic diagram Fig. 1 of the method and apparatus of machine " patent of invention).

As shown in Fig. 1, rotor 1 is a hollow disk, has three pieces spiral shape in the outer surface of the wheel rim (rim) of disk Partition (strake) 2 tiltedly reaches the exhaust side end face of disk from the air inlet side end face of disk with 5 °~10 ° of oblique angle.By circle Angle on week: every partition is 160 degree, and the head of air inlet endplate and the tail portion of exhaust endplate are at a distance of 40 degree, in this area Between disk wheel rim on, arrange compression ramp (compression ramp) 4 and subsonic diffuser (subsonic diffuser)5。

As shown in Fig. 2, the inner surface of the partition (Fig. 2 inconvenience indicates, sees the piece number 2 of attached drawing 1) of disk two sides, rotor wheel The outer surface of edge 3 and the inner surface of casing 6, form the cavity of rectangular cross section, as three sections of uniformly distributed in a circumferential direction gases Channel.

The head of front and back partition is unlimited at a distance of 120 degree, and non-inductive windings block, the inlet port as gas (in inlet end) With outlet (in exhaust end), axial admission turn 90 degrees and becomes by the static entry guide vane of disk inlet end one circle of side setting Enter gas passage after circumferencial direction.The air-flow of outlet enters spiral case through the channel on casing, and part kinetic energy is become pressure Energy.

As shown in 2 rotor gas passage figure of Figure of description, there are three sections of gas passages in the outer circle of rotor, every section of channel accounts for According to 120 degree, it is divided into contraction section 1 and expansion segment 8.The inner surface of casing 5 is cylindrical shape, and the sectional area of contraction section 1 gradually reduces, and is expanded The sectional area for opening section 8 gradually expands, and two sections of junction sectional areas are minimum, referred to herein as throat 4.

Because the cross section of contraction section 1 gradually reduces, gas velocity is stepped up, and rotor rim 3 is inclined outwardly, and radius becomes suddenly Greatly, tangential peripheral speed increases suddenly.Because airflow direction and rotor turn on the contrary, the relative velocity of air-flow and rotor be gas velocity with The vector sum of compression ramp tangential velocity.When the relative velocity of air-flow is more than velocity of sound under gaseous state herein, compression ramp Place generates oblique shock wave beam (oblique shock system) 2, carries out shock wave compression to air-flow, and stream pressure sharply increases, temperature Degree sharply increases.

After throat 4 enters the expansion segment 8 of gas passage, gas velocity gradually slows down air-flow, and sharply because of gas temperature It increases, the velocity of sound in gas also significantly increases, and the ratio (relative Mach number) of air-flow relative velocity and velocity of sound is less than 1, air-flow Speed-shifting is subsonic speed, and the part kinetic energy of air-flow is changed into pressure energy again, and the discharge pressure of gas further increases.

According to the above-mentioned basic principle of shock wave compression, the airflow direction of supersonic compressor should be turned to rotor on the contrary, making The relative velocity of air-flow and rotor be air velocity and rotor peripheral speed vector sum (because the two is not arranged on the same straight line, Vector sum is slightly less than algebraical sum).Both if airflow direction is identical as rotor steering, the relative velocity of air-flow and rotor is exactly Phasor difference slows down air-flow relative velocity, may influence whether air-flow relative velocity can meet or exceed gas at compression ramp Velocity of sound under body state.

Act on the axial force on rotor about gas: in the outer circle of rotor inside gas passage, partition medial surface by Gas pressure be self-balancing, but rotor exhaust end, the axial gas forces that partition lateral surface is subject to, be rotor lateral surface by Power area is multiplied by pressure at expulsion；Rotor inlet end, the axial gas forces that partition lateral surface is subject to are the stress surfaces of rotor lateral surface Product is multiplied by admission pressure；The difference of the two is the axial force that gas acts on rotor.

The United States Patent (USP) and Chinese patent of supersonic compressor are mainly by Ramgen company, the U.S. and General Electric Co. Limited's (letter Claim GE) it is all.

It is to be solved to face three big technical problems for supersonic compressor technology at present:

First is that how to realize that the outlet pressure of supersonic compressor reaches 50MPa；

Second is that the method and apparatus of starting supersonic compressor；

Third is that hyperpressure, the axial force balance of ultrahigh rotating speed rotor and bearing type.

Ramgen company " supersonic compressor " patent US 7,334,990,2008.2.26 is authorized, Figure 16, and two are turned On a shaft, the axial force of two rotors is balanced for sub- parallel connection, mitigates tens of thousands of turns per minute of bearing load.Two completely Identical rotor is connected in parallel on same axis, and flow doubles, but compressor is one stage of compression, and pressure ratio is limited, is not able to satisfy completely " CCS " and " CO₂The requirement of-EOR " project.Another defect is, driving machine will be coupled by stretching place because of axis, and the air inlet of compressor is from two A radial adapter tube enters, and rotor air inlet is unevenly distributed, and efficiency decreases.

Chinese patent " supersonic compressor " CN 102,865,234A of La Mu King Company, 2013.1.9 are announced, specification Last page Figure 34 increases two-stage supersonic compressor schematic diagram, but existing defects:

1. delivery temperature is very high because the pressure ratio of the first order 408 is very big, the velocity of sound in gas is increased, if the second level The ratio of the relative velocity of 414 air-flows and rotor and velocity of sound, i.e. relative Mach number cannot generate shock wave less than 1, not have out The condition of existing shock wave compression.It can be seen that heat exchanger should be arranged in the outlet of the first order.

2. two rotors are identical by the axial force direction of gas, it is all directed to step-up gear 404, the sum of axial force is very Greatly, it to be born by the thrust bearing on the pinion shaft of gear-box, and the revolving speed of pinion shaft is up to tens of thousands of RPM, increases The difficulty of ultrahigh speed, heavy load thrust bearing type selecting.

Above-mentioned Chinese patent Figure 34 La Mu King Company 7,334,990 supersonic compressor of United States Patent (USP) US and US 7, It is all not present in 293,955 supersonic gas gas compressors, it appears that have the suspicion for misleading the imitated person of China.

GE company " supersonic compressor " Chinese invention patent CN 101,813,094B, 2013.8.14 authorization, right are wanted The supersonic compressor rotor for asking 1:.... at least two to reversely rotate is configured to connect.(this indicates two stages of compression).

The first and second supersonic compressor rotor of claim 2:.... is substantially identical, is of similar shape, again Amount and diameter, there is the wheel rim surface feature of same type and identical quantity ... is in mirror image each other.

If it is desired that the peripheral speed direction at first order rotor outlet airflow direction and second level rotor compression inclined-plane 220 On the contrary, need to just increase the entry guide vane of mat woven of fine bamboo strips second level between two-stage rotor, the exhaust turnback of mat woven of fine bamboo strips level-one is made to enter mat woven of fine bamboo strips second level, but The entry guide vane of the second level is not represented on this patent specification attached drawing 1.

GE company inventor thinks that two-stage rotor inverts, the relative velocity of second level rotor and the speed relatively of first order rotor Degree can be added, therefore, have to by two rotors be dimensioned to it is identical.

Peripheral speed at 200 compression ramp 220 of second level rotor be by this grade of rotor compression inclined-plane 220 radius and What revolving speed determined, it is unrelated with first order rotor 100, and two rotors of non-inverted bump against；Also, gas is in two-stage rotor flow tract In flowing, like on highway with respect to traveling automobile, take their own roads, will not bump against.

The weight flow of two-stage rotor gas is identical, and on GE specification, the pressure ratio acquirement of the first order is smaller, and pressure ratio is 5, It is included in the raising of first order delivery temperature, the volume flow of second level air inlet only has the 1/3.41 of the first order, because of the ruler of two rotors Very little identical, air velocity just only has the 1/3.41 of the first order.

Why must be provided with gas heat exchanger between the grade of supersonic compressor, calculated about the velocity of sound in gas:

C=(k.R.T/M)^0.5

In formula: mono- velocity of sound of C, m/s；

The adiabatic exponent or specific heat ratio Cp/Cv of mono- gas of k；

Mono- gas constant of R；

Mono- absolute temperature of T, K；

The molecular weight of mono- gas of M.

CO₂The adiabatic exponent k=1.29 of gas, molecular weight M=44, the velocity of sound C=of standard state (1bar.A, 20 DEG C) 268.2m/s。

The pressure ratio 1.5 or so of conventional centrifugal compressor one stage impeller, gas temperature rise is limited after compression, can only be arranged cold between section But device, the heat of compression enter cooling water, and the heat of compression is discharged in atmosphere through circulating water cooling tower.And supersonic speed CO₂Compressor level-one The pressure ratio 10 or so of impeller, also can reach 18,248 DEG C to 328 DEG C of gas outlet temperature after compression, therefore heat transfer temperature difference is very big, Heat exchanger heat transfer area can reduce, and gas heat exchanger is arranged between grade, and the recycling heat of compression is raw for industry such as boiler feedwater preheatings Liquid heating in production.

More it is essential that as, without heat exchanger, the intake air temperature of rear class is high, the velocity of sound substantial increase in gas between grade, If the relative velocity on gas velocity and rotor compression inclined-plane is lower than velocity of sound, i.e. relative Mach number cannot generate shock wave, no less than 1 Has the condition for realizing shock wave compression.

From above formula it is found that the velocity of sound in gas is directly proportional to the square root of gas absolute temperature, because of the insulation of same gas Index and gas constant variation are small.For example, 255 DEG C of outlet temperature of CO₂Gas, which does not cool down, enters next stage rotor, temperature (273 + 255=528) K CO₂The velocity of sound C=(528 ÷ 293) of gas^0.5× 268.2=360m/s.Such as the CO of outlet₂Gas is used to heater After liquid in industry production, temperature is reduced to 60 DEG C, CO₂The velocity of sound of gas will reduce, C=(333 ÷ 293)^0.5× 268.2= 285.9m/s, i.e. velocity of sound reduce 74.1m/s, not only contribute to the smooth starting of supersonic compressor, also as Mach number increases Greatly, the rotor compression under the same terms is than increasing.

The above-mentioned patent of GE company, because two-stage rotor is close together, no intercooler, second level intake air temperature is very high, Velocity of sound in gas will increase, and the relative velocity of second level air-flow and rotor has slowed down very much, the ratio of it and velocity of sound, i.e., Relative Mach number, such as less than 1, cannot generate shock wave, not have the condition for realizing shock wave shock wave compression.

GE company patent of invention CN 101,813,094B, claim 8, " Supersonic ram compression according to claim 1 Contracting machine, which is characterized in that including at least three supersonic compressor rotors ".Does is rotor three stage compression no figure can determine whether. It inquires the corresponding United States Patent (USP) US 8,137,054,2012.3.20 of GE company supersonic compressor to authorize, just know on Chinese patent Fig. 4 B of United States Patent (USP) is not announced.It just confirmed that these three rotors are still two stages of compression, Fig. 4 B of the United States Patent (USP) from Fig. 4 B Also defective:

(1) " claim 8, supersonic compressor according to claim 1, including at least three supersonic compressions Machine rotor ".Three supersonic compressor rotors are represented on Fig. 4 B: first order rotor 100 is one, and second level rotor 200 is Two.Volume-diminished after one first order rotor gas compression supplies two second level rotors again, and second level rotor gas velocity is very It is low, influence whether oblique shock wave can generate；

(2) on the contrary, without entry guide vane between two-stage rotor, cannot achieve gas flow should change for the steering of two-stage rotor 180 degree.

Three step-up gears and three motor will be arranged in (3) three rotors.

As described above, the patent of invention of Ramgen company only discloses the supersonic compressor of one stage of compression, Chinese patent " supersonic compressor " increases two-stage supersonic compressor schematic diagram, existing defects.The two-stage supersonic compressor of GE company is deposited In above-described defect.Therefore, the technical problem that how supersonic compressor outlet pressure reaches 50MPa at present waits to solve Certainly.

Technical problem to be solved second is that the method and apparatus of starting supersonic compressor.

The precondition for generating shock wave compression is that the air-flow relative velocity in inlet channel should meet or exceed velocity of sound, and Do not have this condition during compressor start, the starting of supersonic compressor is one of critical technical problem.La Mujin " method and apparatus of starting supersonic compressor " CN 101,918,719B of company, Chinese invention patent 2013.10.2 are awarded Power, it is more exact that " the Method and apparatus for of United States Patent (USP) US 8,152,439 of Ramgen company Starting supersonic compressors ", 2012.4.10 authorization.It is US that this specification attached drawing 2, which is by United States Patent (USP), 8,152,439 Fig. 1 and Fig. 6 merges, and refines out crucial piece number and figure forms, in order to understand the starting of supersonic compressor Method.The method that the patent uses is: setting bypass pumping dress on the casing before compressor air intake duct contraction section compression ramp It sets, in compressor acceleration period, by compressed portion gas through bypass gas collection chamber 5, bypass 9, return valve 10, reflux To compressor inlet, increase charge flow rate, air velocity is improved, to realize the foundation of supersonic speed shock wave.Once it is selected into Under mouth relative Mach number and pressure ratio, after oblique shock wave system stablizes, return valve 10 is closed with bypass reflux control system 11, just Without reflux when often operation.Another benefit using bypass pumping is to take the boundary-layer on gas flow wall away, is reduced attached Surface layer and shock wave interfere with each other.

The shortcomings that the method is part medium pressure gas to be flowed back into compressor inlet through bypass, the energy during causing to start Amount waste.

La Mu King Company patent of invention CN101,918,719B " method and apparatus of starting supersonic compressor ", Fig. 3 is The relationship of pumping and air inlet weight flow ratio when entrance relative Mach number and starting, Fig. 4 is that different entrance relative Mach numbers can It is as follows to be merged into form by the compression ratio reached for this two width figure.It can be seen that from this table, when supersonic compressor starts, take out Gas regurgitant volume is bigger, indicates that the speed of gas in rotor air inlet runner can increase as early as possible, entrance relative Mach number is bigger, accordingly Ground can reach higher compression ratio, improve the performance of supersonic compressor.

GE company " supersonic compressor starts support system and related starting method " CN 103,620,226B, 2016.8.17 authorization.

This patent specification attached drawing 8 pushes 178 axial stretching of pane, during making compressor start, larynx with hydraulic mechanism 124 area of portion increases, and reduces the flow resistance at throat, to increase charge flow rate, improves air velocity；When normal operation, Hydraulic mechanism pushes pane 178 to protrude into throat perpendicular to airflow direction, reduces throat opening area, and pane 178 is not streamlined, There is the pressure loss in gas flow for a long time.Because compressor gas supplied changes in flow rate is small, increase the stream of air inlet runner with this scheme It measures very limited.Hydraulic mechanism (hydraulic oil storage tank 182, hydraulic cylinder 184, hydraulic piston 190 etc.) will be revolved with 158 high-speed synchronous of rotor Turn, axial stretching, rotor dynamic balancing precision will become greatly again, cause judder.This scenario-frame is complicated, technically can not Row.

Technical problem to be solved third is that hyperpressure, the axial force balance of ultrahigh rotating speed rotor and bearing type.

It is all not directed in the supersonic compressor patent of the U.S. and China, may is that and refuse public affairs as know-how Open, but this can be that supersonic compression is confidential industrially securely and reliably operate, it is necessary to the technical issues of solving.

Supersonic compressor rotor exhaust end, the axial gas forces that partition lateral surface is subject to are the stress of rotor lateral surface Area is multiplied by pressure at expulsion；Rotor inlet end, the axial gas forces that partition lateral surface is subject to are the forced areas of rotor lateral surface Multiplied by admission pressure；The difference of the two is the axial force that gas acts on rotor.For the rotor of hyperpressure, this axial direction Power is very big.7,334,990 Figure 16 of Ramgen company " supersonic compressor " patent US, by two rotors it is back-to-back be mounted on it is same On a piece axis, the axial force of two rotors is balanced.The bush(ing) bearing of high revolving speed rotor cannot bear any axial force, It must be provided with hydrodynamic thrust bearing, higher cost.

Summary of the invention

It is an object of the invention to: for existing supersonic compressor, providing one kind be can satisfy Ultra-deep oil reservoir exploits the CO for answering injection pressure to be up to 50MPa₂The demand of gas, to promote low cost, super-pressure CO₂Compressor exists The supersonic speed super-pressure carbon-dioxide gas compressor of industrial applications in " carbon capture with seal up for safekeeping " and " raising oil recovery factor " project Unit comes out early.

To achieve the above object, the invention adopts the following technical scheme: supersonic speed super-pressure carbon-dioxide gas compressor unit, Including inlet casing, pre- propeller runner, entry guide vane, rotor, exit casing, step-up gear, shaft coupling and motor, feature It is: using three-level supersonic speed shock wave compression, by the first order shock wave compression component of sub-high pressure, the second level shock wave compression of high pressure The third level shock wave compression component of component and super-pressure composition, the first order shock wave compression component of the sub-high pressure is by symmetrical cloth Two groups of sub-high pressure shock wave compression units composition in the first pinion shaft end and parallel running are set, the second level of the high pressure is swashed Wave compression assembly is made of two groups of high pressure shock wave compression units for being arranged symmetrically in the second pinion shaft end and parallel running, institute The third level shock wave compression component of super-pressure is stated by being arranged in one group far from motor side corresponding end of third pinion axis Super-pressure shock wave compression unit composition.

Supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, the first order shock wave pressure of the sub-high pressure Between contracting component and the second level shock wave compression component of high pressure and the second level shock wave compression component of high pressure and super-pressure Gas heat exchanger is provided between three-level shock wave compression component.

Supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, the first order shock wave pressure of the sub-high pressure Setting bypass is taken out on casing before the air intake duct contraction section compression ramp of contracting component and the second level shock wave compression component of high pressure Compressed portion gas is flowed back into compressor inlet during compressor start by device of air, establishes supersonic speed shock wave, once After oblique shock wave system stablizes, return valve closed by bypass reflux control system, without reflux when normal operation；And third Grade is one group of super-pressure shock wave compression unit, is supplied from two groups of second level high pressure shock wave compression units to it, is not provided on casing Bypass air extractor.

The shock wave compression component of supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, three of them grade is corresponding Rotor in shock wave compression unit is connected with corresponding pinion shaft end respectively, the air-flow of the shock wave compression component of three grades The steering of the corresponding rotor in direction is opposite.

The shock wave compression component of supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, three of them grade is corresponding Together with inlet casing, rotor casing in shock wave compression unit are bolted with body, then it is fixed to step-up gear On outer wall.

Supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, entire supersonic speed super-pressure carbon dioxide Compressor Group uses a motor, a step-up gear and a set of diaphragm coupling.

Supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, the first order shock wave pressure of the sub-high pressure It is in parallel that contracting component and the second level shock wave compression component of high pressure are all made of two rotors being arranged symmetrically, and back-to-back is mounted on pair The both ends of pinion shaft are answered, a rotor of the third level shock wave compression component of the super-pressure is mounted on corresponding pinion shaft End, five rotors are axial admission.

Supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, in the three-level shock wave compression component, The root diameter in shock wave compression component from the first order to the third level gradually successively decreases and revolving speed is incremented by, in three-level shock wave compression group Pinion gear is respectively arranged on pinion shaft in part, three pinion gears in the three-level shock wave compression component respectively with speedup Gear wheel engagement in gear-box, drives three pinion gears by a gear wheel simultaneously.

Supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, the gear wheel and pinion gear at different levels Gear ratio is non-integer, the number of teeth of each pair of meshing gear prime number each other.

Supersonic speed super-pressure carbon-dioxide gas compressor unit of the present invention, in the gear wheel and corresponding pinion gear The pitch circle that relative velocity is zero is nearby provided with bidirectional propulsion disk, and there are six thrust discs for setting on three pinion shafts, described to push away There is 2 °~3 ° of small gradient in the side of power disk.

Compared with prior art, the present invention having the benefit that

1. there was only one stage of compression using the supersonic compressor structure of shock wave compression technology both at home and abroad at present, and two stages of compression Supersonic compressor there are technological deficiencies, be not able to satisfy " CO₂- EOR " project is to 50MPa super-pressure CO₂The demand of compressor. The present invention installs the supersonic speed super-pressure CO of 5 rotors on a gear-box₂Compressor forms three-level shock wave compression, final stage Export CO₂The pressure of gas can achieve 50MPa or so, and the peripheral speed of rotor is 428~439m/s, allow than mechanical limit 730~914m/s of rotor peripheral speed (material depending on rotor) it is sufficiently low, safety is very high.Meet the exploitation of ultra-deep oil reservoir Injection pressure is answered to be up to the CO of 50MPa₂The demand of gas promotes low cost, super-pressure CO₂Compressor is in " carbon capture and seal up for safekeeping " Industrial applications in " improving oil recovery factor " project.

2. to solve the technical problem of supersonic compressor starting difficulty, the first order of sub-high pressure and the second level of high pressure turn The starting of son, the bypass for using for reference the invention of Ramgen company is evacuated technique of backflow, in compressor acceleration period, by compressed part Gas backstreaming increases charge flow rate to compressor inlet, air velocity is improved, to realize the foundation of supersonic speed shock wave.Once tiltedly After multishock is stablized, return valve closed with bypass reflux control system, without reflux when normal operation.To avoid superelevation The third level of pressure rises and employs return schemes, the energy dissipation during causing to start, by two groups of second level high pressure shock wave compression units It is supplied to it.

3. five rotors are installed in the end of pinion shaft, dismounting rotor is convenient, and axial admission is uniform, overcomes existing Driving machine will be coupled by stretching place because of axis in structure, and the air inlet of compressor will enter from two radial adapter tubes, and rotor air inlet is unevenly distributed, The defect that efficiency decreases.

4. bidirectional propulsion disk is arranged near the pitch circle that gear wheel and pinion gear relative velocity are zero, by high revolving speed or superelevation The axial force of lack of equilibrium passes on two sides of gear wheel on the pinion shaft of revolving speed, then passes to the thrust of middling speed Large Gear Shaft On bearing, therefore, time high speed, high speed and the ultrahigh speed thrust bearing of all pinion shafts is eliminated, the function of thrust bearing is reduced Consumption, and axial displacement monitor need to be only set in middling speed Large Gear Shaft, improve supersonic compressor maintainability.

Detailed description of the invention

The accompanying drawings constituting a part of this application is used to provide further understanding of the present invention, tool of the invention Body embodiment and its explanation are used to explain the present invention, and are not constituted improper limitations of the present invention.

Fig. 1 is supersonic compressor rotor schematic diagram (Ramgen company " supersonic compressor " the patent US of the prior art 7,334,990)。

Label in Fig. 1: 1 is rotor；2 be partition strakes；3 be air intake duct surface；4 be compression ramp compression ramp；5 be subsonic diffuser subsonic diffuser.

Fig. 2 is the rotor gas flow and bypass reflux schematic diagram (La Mu King Company CN 101,918,719B of the prior art Fig. 1 of " method and apparatus of starting supersonic compressor " patent of invention).

Label in Fig. 2: 1 is the contraction section of air intake duct；2 be oblique shock wave beam oblique shock system；3 be rotor Wheel rim rim；4 be throat；5 be bypass gas collection chamber；6 be casing；7 be normal shock wave normal shock；8 be the expansion of air intake duct Section；9 be bypass；10 be return valve；11 be bypass reflux control system.

Fig. 3 is three-level supersonic speed CO of the invention₂Compressor set plan view.

Label in Fig. 3: 1 is first order inlet casing；2 be the pre- propeller runner of the first order；3 be first order entry guide vane；4 are First order rotor；5 be first order rotor casing；6 be first order body and exhaust volute；7 be the first pinion shaft；8 be speedup Gear-box；9 slide for the first transverse bearing；10 be the first pinion gear；11 be first order thrust disc；12 be First Heat Exchanger；13 For second level inlet casing；14 be the pre- propeller runner in the second level；15 be second level entry guide vane；16 be second level rotor；17 be Secondary rotor casing；18 be second level body and exhaust volute；19 be the second pinion shaft；20 be the second bush(ing) bearing； 21 be the second pinion gear；22 be second level thrust disc；23 be the second heat exchanger；24 be third level inlet casing；25 be the third level Pre- propeller runner；26 be third level entry guide vane；27 be third level rotor；28 be third level rotor casing；29 be third level body And exhaust volute；30 be third pinion axis；31 be third bush(ing) bearing；32 be third pinion；33 push away for the third level Power disk；34 be gear wheel；35 be bush(ing) bearing；36 be thrust bearing；37 be Large Gear Shaft；38 be shaft coupling；39 be electricity Motivation.

Fig. 4 is three-level supersonic speed CO of the invention₂Compressor three-dimensional figure.

Label in Fig. 4: 1 is first order inlet casing；5 be first order rotor casing；6 be first order body and exhaust snail Shell；8 be step-up gear；13 be second level inlet casing；17 be second level rotor casing；18 be second level body and exhaust snail Shell；24 be third level inlet casing；28 be third level rotor casing；29 be third level body and exhaust volute；32 is small for third Gear；33 be third level thrust disc；34 be gear wheel.

Specific embodiment

The present invention is quantitatively deeply understood in order to become apparent from, and now using this specification attached drawing 3 as example, is provided using the present invention Detailed technology scheme.

Certain offshore production platform ultra-deep oil reservoir recovers the oil, and need to inject the CO of 52MPa.A pressure₂Gas, Compressor Inlet Pressure are 0.13MPa.A.Using three-level supersonic speed CO₂0.32MPa is pressed in the pressure drop of compressor set scheme, two intercoolers, is equivalent to Final stage outlet pressure is 52.32MPa.A, overall pressure tatio 402.46.About the allocation plan of pressure ratios at different levels, in order to make final stage rotor Diameter be unlikely to too small, the pressure ratio of chopped-off head is obtained less than normal, the pressure ratio of final stage obtains larger, and pressure ratios at different levels are successively are as follows: 6.8, 7.3、8.11。

Super-pressure supersonic speed CO as shown in Fig. 3₂Compressor, including inlet casing, pre- propeller runner, entry guide vane, turn Son, exit casing, step-up gear, shaft coupling and motor use three-level supersonic speed shock wave compression, by the first of sub-high pressure The third level shock wave compression component composition of grade shock wave compression component, the second level shock wave compression component of high pressure and super-pressure, it is preceding Two-stage is operated by two groups of shock wave compression modules in parallel, and the third level of super-pressure is one group of shock wave compression component, i.e., of the invention Super-pressure supersonic speed CO₂Compressor is with the compressor set of five groups of shock wave compression components composition three-level shock wave compression, by with two The group second level supply to one group of third level, avoid superelevation arbitrarily downgrade flowed back during rotor starting with high pressure gas caused by energy it is unrestrained Take.

Wherein, the first order shock wave compression component of the sub-high pressure is by being arranged symmetrically in the two of 7 end of the first pinion shaft Group sub-high pressure shock wave compression unit composition and parallel running, every group of sub-high pressure shock wave compression unit include first order inlet casing 1, The pre- propeller runner 2 of the first order, first order entry guide vane 3, first order rotor 4, first order rotor casing 5 and first order body and exhaust Spiral case 6.The first order inlet casing 1, first order rotor casing 5 and first order body and exhaust volute 6 be connected with for One, then is fixed on the outer wall of step-up gear 8 with studs, and the pre- propeller runner 2 of the first order and first order rotor 4 are solid Be scheduled on the end of the first pinion shaft 7, the first order entry guide vane 3 is static element, be fixed on first order rotor casing 5 into Gas end.

The second level shock wave compression component of the high pressure is by being arranged symmetrically in two groups of high pressures of 19 end of the second pinion shaft Shock wave compression unit composition and parallel running, every group of high pressure shock wave compression unit include that second level inlet casing 13, the second level are pre- Propeller runner 14, second level entry guide vane 15, second level rotor 16, second level rotor casing 17 and second level body and exhaust volute 18.The second level inlet casing 13, second level rotor casing 17 and second level body and exhaust volute 18 be connected with for One, then is fixed on the outer wall of step-up gear 8 with studs, the pre- propeller runner 14 in the second level and second level rotor 16 It is fixed on the end of the second pinion shaft 19, the second level entry guide vane 15 is static element, is fixed on second level rotor casing 17 inlet end.

The third level shock wave compression component of the super-pressure is by being arranged in third pinion axis 30 far from 39 side of motor One group of super-pressure shock wave compression unit of corresponding end forms, and the super-pressure shock wave compression unit includes third level inlet casing 24, the pre- propeller runner 25 of the third level, third level entry guide vane 26, third level rotor 27, third level rotor casing 28 and third level machine Body and exhaust volute 29.The third level inlet casing 24, third level rotor casing 28 and third level body and exhaust volute 29 It is connected with and is integrated, then be fixed on the outer wall of step-up gear 8 with studs, pre- 25 He of propeller runner of the third level Third level rotor 27 is fixed on the end of third pinion axis 30, and the third level entry guide vane 26 is static element, is fixed on The inlet end of three-level rotor casing 28.

In the present embodiment, the second level shock wave compression component of the first order shock wave compression component of the sub-high pressure and high pressure Between be provided with First Heat Exchanger 12, the second level shock wave compression component of the high pressure and the third level shock wave compression group of super-pressure The second heat exchanger 23 is provided between part.The sub-high pressure CO being discharged from two groups of first order bodies and exhaust volute 6₂Gas summarize for Enter First Heat Exchanger 12 after one pipeline, because of supersonic speed CO₂Compressor single-stage pressure ratio is big, and delivery temperature is more centrifugal than traditional Compressor is much higher, it is necessary to reduce the temperature of gas, otherwise the velocity of sound in high-temperature gas will increase, and be unfavorable for generating shock wave；Separately Outside, because delivery temperature is high, it can be used to preboiler water supply, the biography of heat exchanger can be reduced by recycling the heat of compression because heat transfer temperature difference is big Heat area.Sub-high pressure CO after the cooling of First Heat Exchanger 12₂Gas enters second level inlet casing 13, from two groups of second level machines The high pressure CO that body and exhaust volute 18 are discharged₂Gas summarizes to enter the second heat exchanger 23 after a pipeline, because of supersonic speed CO₂Pressure Contracting machine single-stage pressure ratio is big, and delivery temperature is more much higher than traditional centrifugal compressor, it is necessary to reduce the temperature of gas, otherwise high temperature Velocity of sound in gas will increase, and be unfavorable for generating shock wave；In addition, can be used to preboiler water supply because delivery temperature is high, recycle The heat of compression can reduce the heat transfer area of heat exchanger because heat transfer temperature difference is big.High pressure CO after the cooling of the second heat exchanger 23₂Gas into Enter to enter third level inlet casing 24.

Entire supersonic compressor unit of the invention only uses 39, step-up gears 8 of a motor and a mantle Piece shaft coupling 38.The root diameter in shock wave compression component in the three-level shock wave compression component, from the first order to the third level Gradually successively decrease and revolving speed is incremented by, keeps the air velocity of later stages sufficiently high, on the pinion shaft in three-level shock wave compression component Be respectively arranged with pinion gear, three pinion gears in the three-level shock wave compression component respectively with the gear wheel in step-up gear Engagement drives three pinion gears by a gear wheel simultaneously.Specifically: the motor 39 drives by diaphragm coupling 38 Gear wheel 34, then the first pinion gear 10, the second pinion gear 21 and third pinion 32 are driven, the two of first pinion shaft 7 End connection first order rotor 4 and the pre- propeller runner 2 of the first order；The both ends of second pinion shaft 19 connect 16 He of second level rotor The pre- propeller runner 14 in the second level；One end connection third level rotor 27 and the pre- propeller runner 25 of the third level of the third pinion axis 30.

Wherein, the first order shock wave compression component of the sub-high pressure and the second level shock wave compression component of high pressure are all made of two A rotor being arranged symmetrically is in parallel, and the back-to-back both ends for being mounted on corresponding pinion shaft, axial force balance, the super-pressure A rotor of third level shock wave compression component be mounted on the end of corresponding pinion shaft, the shock wave compression group of three grades The steering of the corresponding rotor of the airflow direction of part is on the contrary, make the relative velocity of air-flow and rotor be air velocity and rotor circumference The vector sum of speed, five rotors are installed in the end of corresponding pinion shaft, and dismounting rotor is convenient, and five rotors are axis To air inlet, make its air inlet uniformity, overcomes and stretch place because of axis in existing structure and to couple driving machine, the air inlet of compressor will be from two Radial adapter tube enters, and rotor air inlet is unevenly distributed, the defect that efficiency decreases.

The both ends of first pinion shaft 7, the second pinion shaft 19 and third pinion axis 30 are respectively supported at two First transverse bearing of a hydrodynamic pattern slides in the 9, second transverse bearing sliding 20 and third transverse bearing sliding 31, by Axial force cannot be undertaken completely in bush(ing) bearing, in order to avoid dynamic using fluid on secondary high speed, high speed and ultrahigh speed axis Press thrust bearing, be respectively set near the pitch circle that three pinion gears and gear wheel relative velocity are zero first order thrust disc 11, Second level thrust disc 22 and third level thrust disc 33 are arranged altogether for the axial force for bearing two-way lack of equilibrium on three pinion shafts Six thrust discs, so that the axial force of pinion shaft lack of equilibrium be passed on two sides of gear wheel 34, then to pass to middling speed big On the thrust bearing 36 of gear shaft 37, therefore, the thrust bearing of all high speeds, high speed and ultrahigh speed pinion shaft is eliminated, The power consumption of thrust bearing is reduced, and axial displacement monitor need to be only set in middling speed Large Gear Shaft 37, improves Supersonic ram compression Contracting machine maintainability, the side of the thrust disc have 2 °~3 ° of small gradient to improve it to form hydrodynamic oil film wedge Bearing capacity.The both ends of Large Gear Shaft 37 are both supported upon on two hydrodynamic bush(ing) bearings 35, and by thrust bearing 36 Undertake the first pinion shaft 7, the axial force that the second pinion shaft 19 and third pinion axis 30 transmit.

According to supersonic speed super-pressure CO₂Compressor Group conceptual design calculated result, the revolving speed of the first pinion gear 10 are 21, 350 revs/min, the revolving speed of the second pinion gear 21 is 32,620 revs/min, and the revolving speed of third pinion 32 is 51,050 rev/min.It is electronic The revolving speed of machine 39 is selected as 2980 revs/min, i.e. the revolving speed of gear wheel 34 is 2980 revs/min, transmission ratio at different levels, i.e., size teeth at different levels The gear ratio of wheel is respectively 7.164,10.946,17.131.The number of teeth of third pinion 32 is taken as 23, the tooth of the second pinion gear 21 Number is 36, and the number of teeth of the first pinion gear 10 is 55, and the number of teeth of gear wheel 34 is 394.The gear ratio of big pinion gears at different levels is non-whole Number, the number of teeth of each pair of meshing gear prime number each other.Share even wearing on all teeth, is conducive to one section of new gear set running-in After time, the tooth form of each tooth tends to its ideal tooth form, guarantees the uniform stressed of uniform wear and the transmission of each tooth, mitigates high The vibration of fast gear engagement and noise.

The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.