CN204553354U - Subtract the gas compressor of scroll and aeroengine - Google Patents
Subtract the gas compressor of scroll and aeroengine Download PDFInfo
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- CN204553354U CN204553354U CN201520136114.9U CN201520136114U CN204553354U CN 204553354 U CN204553354 U CN 204553354U CN 201520136114 U CN201520136114 U CN 201520136114U CN 204553354 U CN204553354 U CN 204553354U
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Abstract
The utility model discloses a kind of gas compressor subtracting scroll and aeroengine, relate to aero engine technology field.Solve prior art to exist and subtract the larger technical problem of the flow losses of whirlpool device.This subtracts scroll and comprises the intake section, straight drum part and the exit portion that are communicated with successively, and intake section, straight drum part and exit portion three are rotation body and the shaft axis of three coincides; The inwall of intake section reduces gradually along entering flow path direction internal diameter size, and the inwall of exit portion increases gradually along going out flow path direction internal diameter size.What the gas compressor of the aeroengine that the utility model provides comprised that the first compressor disc, the second compressor disc, drum barrel and at least one the utility model provide subtracts scroll.The air current flow loss that the utility model causes for reducing scroll, improves the working efficiency of gas compressor.
Description
Technical field
The utility model relates to aero engine technology field, particularly relates to a kind of gas compressor subtracting scroll and arrange that this subtracts the aeroengine of scroll.
Background technique
In aviation turbofan engine, in order to cooling down high-temperature parts (as firing chamber, high-pressure turbine) and obturage bearing bore and turbine disk chamber, need from high-pressure compressor bleed.The stream form of the air system radial inward flow bleed of the motor that present stage is comparatively advanced is: first from the perforate of high-pressure compressor drum barrel, cooled gas is made to enter high-pressure compressor dish chamber, then flow in the chamber, axle center at core place, flow to motor rear portion by chamber, axle center.Because cooled gas flows to low radial location from the high radial location in high-pressure compressor inside rotating disc cavities, free vortex structural strength strengthens gradually, cause very large flow losses, effectively can weaken the development of vortex structure by installing the mode subtracting whirlpool device, thus effectively reduce the pressure loss.
At present, the conventional whirlpool device structure that subtracts is that tubular type subtracts whirlpool device (or claim: subtract scroll), existing a kind of tubular type subtracts its upper end of device structure, whirlpool and is directly connected in drum barrel hole place, the gas of such high-pressure compressor sprue is flowed directly in center cavity after entering and subtracting scroll, no longer by the inside rotating disc cavities of high-pressure compressor, this just causes cooled gas to arrive in chamber, axle center with forced vortex state, not through the development of free vortex, loses relatively large.
Existing another kind of tubular type subtracts whirlpool device structure, this subtracts whirlpool device inlet end is cantilever structure, through the development of one section of free vortex after cooling blast enters high-pressure compressor inside rotating disc cavities from drum barrel hole, enter and subtract in the device of whirlpool, the structural pressure loss being directly connected in drum barrel place compared to upper end wall is little, but it is less to subtract scroll inlet end caliber, cooling blast flows at a certain angle and subtracts in scroll, impact tube wall and form recirculating zone, cause the actual discharge coefficient at mouth of pipe place lower, loss increases.In addition, in outlet port, lower end, gas flow rate is higher, for avoiding the direct impacting shaft chambers of the heart of air-flow and making air-flow flow backward vertically, generally can install deflection plate additional, subtract scroll exit flow and directly impact on deflection plate, can cause larger flow losses.
Another tubular type existing subtracts whirlpool device structure and notices the loss subtracting scroll outlet end gas and cause the impact of deflection plate, flow guide device is added in this position, but the increase of this structure makes to subtract whirlpool device and forms eccentric structure, vibration can be caused when high speed rotating to strengthen, reduce system reliability.
The applicant finds: prior art at least exists following technical problem:
The existing topmost function of whirlpool device that subtracts is exactly reduce the flow losses of cooled gas in high-pressure compressor dish chamber, (English can be translated as: rotatingratio to subtract the ingress flow rotation ratio of whirlpool device, speed ratio is for representing the ratio of the circumferential speed of air-flow and periphery of rotor speed) with the change of engine operating condition, the moment changes, vertically can not enter and subtract whirlpool device, but enter at a certain angle, cause larger flow losses.In addition, also larger flow losses can be caused subtracting the impact of cooling blast to chamber, axle center deflection plate of device outlet port, whirlpool.
Model utility content
One of them object of the present utility model proposes a kind of gas compressor subtracting scroll and arrange that this subtracts the aeroengine of scroll, solves prior art and exist and subtract the larger technical problem of the flow losses of whirlpool device.Many technique effects that optimal technical scheme in many technological schemes that the utility model provides can produce (structure subtracting scroll is simple, be convenient to manufacture, with low cost, be convenient to dismounting and the advantage such as positional stability is good) refer to and hereafter set forth.
For achieving the above object, the utility model provides following technological scheme:
What the utility model embodiment provided subtracts scroll, comprises the intake section, straight drum part and the exit portion that are communicated with successively, wherein:
Described intake section, described straight drum part and described exit portion three are rotation body and the shaft axis of three coincides;
The inwall of described intake section reduces gradually along entering flow path direction internal diameter size, and the inwall of described exit portion increases gradually along going out flow path direction internal diameter size.
As the further optimization of arbitrary technological scheme that the utility model provides above or hereinafter, the inwall of described intake section and the inwall of described exit portion are the conical surface.
As the further optimization of arbitrary technological scheme that the utility model provides above or hereinafter, the inwall of described intake section and the angle of described shaft axis are 15 ° ~ 30 °.
As the further optimization of arbitrary technological scheme that the utility model provides, described in described intake section is of a size of on the described axial direction subtracting scroll, subtract 1/4 ~ 1/5 of the axial dimension of scroll above or hereinafter.
As the further optimization of arbitrary technological scheme that the utility model provides above or hereinafter, the inwall of described straight drum part is consistent along its axial direction each section of cross-sectional dimension, and the area of the maximum cross section of the inwall of described intake section is 2 ~ 3 times of the area of the cross section of the inwall of described straight drum part.
As the further optimization of arbitrary technological scheme that the utility model provides above or hereinafter, the inwall of described exit portion and the angle of described shaft axis are 30 ° ~ 45 °.
As the further optimization of arbitrary technological scheme that the utility model provides, described in described exit portion is of a size of on the described axial direction subtracting scroll, subtract 1/8 ~ 1/10 of the axial dimension of scroll above or hereinafter.
As the further optimization of arbitrary technological scheme that the utility model provides above or hereinafter, described in subtract scroll and also comprise retainer, described retainer is fixedly connected with the outer wall of described straight drum part, and described retainer is provided with mounting hole and defining flange.
As the further optimization of arbitrary technological scheme that the utility model provides above or hereinafter, the outer wall of described retainer and described exit portion abuts against close to the side of described intake section.
As the further optimization of arbitrary technological scheme that the utility model provides above or hereinafter, described retainer also comprises support body portion and joint, wherein:
Described mounting hole is arranged on described joint, and the axial direction of described mounting hole and the described axial direction subtracting scroll perpendicular;
Described support body portion is fixedly connected with described straight drum part, and the maximum bearing of trend in described support body portion and described shaft axis perpendicular;
Described joint extends along the direction paralleled with described shaft axis towards the direction close to described intake section;
Described defining flange extends along the direction paralleled with described shaft axis towards the direction close to described exit portion.
The gas compressor of the aeroengine that the utility model embodiment provides, what comprise that the first compressor disc, the second compressor disc, drum barrel and the arbitrary technological scheme of at least one the utility model provide subtracts scroll, wherein:
Described drum barrel is connected between described first compressor disc and described second compressor disc;
Described first compressor disc is installed with chamber, axle center deflection plate, described drum barrel is provided with drum barrel hole;
The described intake section subtracting scroll towards described drum barrel hole, described in subtract the exit portion of scroll towards chamber, described axle center deflection plate, the air flow energy flowed out from the described exit portion subtracting scroll enters the chamber, axle center of described gas compressor through chamber, described axle center deflection plate;
The described scroll that subtracts is fixedly connected with described first compressor disc and/or described second compressor disc.
Based on technique scheme, the utility model embodiment at least can produce following technique effect:
The intake section of what the utility model provided subtract scroll is that the circulation area of the air-flow at the air flow inlet place that structure (being preferably taper tapered configuration) this structure of convergent is formed is larger, and the inwall of this intake section can play certain leading role to air-flow, the air-flow making speed ratio be not equal to 1 is subject to the constraint of the inwall (this inwall can be understood as expansion profile) subtracting spiral inlet part convergent, speed ratio is transitioned into 1 gradually and radially flows to the axle center of gas compressor, so the flow losses of the air-flow of inflow can be reduced, simultaneously, the exit portion subtracting scroll is that the circulation area of the air flow outlet air-flow that the structure of flaring (being preferably taper flaring structure) this structure is formed is larger, so the flow expansion of outflow can be made to slow down, and then decrease the flow losses of air-flow to the impact force of chamber, axle center deflection plate and the air-flow of outflow, exist subtract the larger technical problem of the flow losses of whirlpool device so solve prior art.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, and form a application's part, schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
The generalized section subtracting scroll that Fig. 1 provides for the utility model embodiment;
The schematic diagram in the dish chamber of the gas compressor of the aeroengine that Fig. 2 provides for the utility model embodiment;
The schematic diagram of the partial structurtes in the dish chamber of the gas compressor of the aeroengine that Fig. 3 provides for the utility model embodiment;
Mark in figure: 1, running shaft; 2, the first compressor disc; 3, chamber, axle center deflection plate; 4, scroll is subtracted; 41, intake section; 42, straight drum part; 43, exit portion; 5, the second compressor disc; 6, retainer; 61, mounting hole; 62, defining flange; 63, support body portion; 64, joint; 7, drum barrel; 70, drum barrel hole.
Embodiment
Content of the present utility model and the distinctive points between the utility model and prior art can be understood below with reference to accompanying drawing Fig. 1 ~ Fig. 3 and word content.Hereafter by accompanying drawing and the mode enumerating embodiment more of the present utility model, the technical solution of the utility model (comprising optimal technical scheme) is described in further detail.It should be noted that: any technical characteristics in the present embodiment, any technological scheme is all one or more in the technical characteristics of plurality of optional or optional technological scheme, cannot exhaustive all alternative technical characteristicss of the present utility model and alternative technological scheme in order to describe succinct to need in presents, also the mode of execution being not easy to each technical characteristics all emphasizes that it is one of optional numerous embodiments, so those skilled in the art should know: arbitrary technology hand portion that the utility model can be provided carries out two or more technology hand portion any of replacing or being provided by the utility model or technical characteristics carries out mutually combining and obtaining new technological scheme.Any technical characteristics in the present embodiment and any technological scheme all do not limit protection domain of the present utility model, protection domain of the present utility model should comprise those skilled in the art do not pay creative work thinkable any alternate embodiments and those skilled in the art two or more technology hand portion any that the utility model is provided or the technical characteristics new technological scheme carrying out mutually combining and obtain.
The utility model embodiment provides that a kind of flow losses are few, structure is simple, be convenient to manufacture, with low cost, be convenient to dismounting and good the subtracting scroll and the gas compressor that this subtracts the aeroengine of scroll is set of positional stability.
Below in conjunction with the elaboration that Fig. 1 ~ Fig. 3 carries out specifically to the technological scheme that the utility model provides.
As shown in FIG. 1 to 3, what the utility model embodiment provided subtract scroll 4 comprises the intake section 41, straight drum part 42 and the exit portion 43 that are communicated with successively, wherein:
Intake section 41, straight drum part 42 and exit portion 43 three are rotation body and the shaft axis of three coincides.The inwall of intake section 41 reduces gradually along entering flow path direction internal diameter size, and the inwall of exit portion 43 increases gradually along going out flow path direction internal diameter size.
The intake section 41 of what the utility model provided subtract scroll 4 is the structure (being preferably taper tapered configuration) of convergent, the circulation area of the air-flow at the air flow inlet place formed due to this structure is larger, and the inwall of this intake section 41 can play certain leading role to air-flow, the air-flow making speed ratio be not equal to 1 is subject to the constraint of the inwall (this inwall can be understood as expansion profile) subtracting scroll 4 intake section 41 convergent, speed ratio is transitioned into 1 gradually and radially flows to the axle center of gas compressor, so the flow losses of the air-flow of inflow can be reduced, the exit portion 43 subtracting scroll 4 is the structure of flaring (being preferably taper flaring structure), the circulation area of the air flow outlet air-flow formed due to this structure is larger, so the flow expansion of outflow can be made to slow down, and then decrease the flow losses of air-flow to the impact force of chamber, axle center deflection plate 3 and the air-flow of outflow.
As the optimization of the arbitrary technological scheme of the utility model, the inwall of intake section 41 and the inwall of exit portion 43 are the conical surface.The conical surface not only structure simple, be convenient to manufacture and with low cost, and its shape is close to streamline, so the flow losses caused air-flow are considerably less.
As the optimization of the arbitrary technological scheme of the utility model, the inwall of intake section 41 and the angle a of shaft axis are 15 ° ~ 30 °.The airflow area at this structure air flow inlet place is comparatively large, and be conducive to the inflow of air-flow, meanwhile, air-flow can transit to straight drum part 42 gradually in the process of the inwall of intake section 41, and the flow losses of air-flow are less.
As the optimization of the arbitrary technological scheme of the utility model, the size h1 of intake section 41 on the axial direction subtracting scroll 4 is that namely the axial dimension subtracting scroll 4 subtracts 1/4 ~ 1/5 of the total pipe range of scroll.This structure can reduce the flow losses of the air-flow of the inwall through intake section 41 further.
As the optimization of the arbitrary technological scheme of the utility model, the inwall of straight drum part 42 is consistent along its axial direction each section of cross-sectional dimension, and the area of the maximum cross section of the inwall of intake section 41 is 2 ~ 3 times of the area of the cross section of the inwall of straight drum part 42.The airflow area at this structure air flow inlet place is comparatively large, is more conducive to the inflow of air-flow.
As the optimization of the arbitrary technological scheme of the utility model, the inwall of exit portion 43 and the angle b of shaft axis are 30 ° ~ 45 °.This structure can make the flow expansion of outflow slow down faster.
As the optimization of the arbitrary technological scheme of the utility model, the size h2 of exit portion 43 on the axial direction subtracting scroll 4 is 1/8 ~ 1/10 of the axial dimension subtracting scroll 4.This structure is while the speed guaranteeing the flow expansion deceleration that can improve outflow further, and ensure that the directivity of effluent stream is better, airflow leaks loss is less.
As the optimization of the arbitrary technological scheme of the utility model, subtract scroll 4 and also comprise retainer 6, retainer 6 is fixedly connected with the outer wall of straight drum part 42, and retainer 6 is provided with mounting hole 61 and defining flange 62.
Mounting hole 61 can be utilized retainer 6 and subtract scroll 4 and be fixed on structural member (being preferably fixed on the snap ring of the first compressor disc 2) in gas compressor.Defining flange 62 1 aspect can play position-limiting action, has stop bit effect, can improve installation efficiency when installing on the other hand.
As the optimization of the arbitrary technological scheme of the utility model, the outer wall of retainer 6 and exit portion 43 abuts against close to the side of described intake section 41.Retainer 6 can apply certain abutting power to exit portion 43, this abutting power can be avoided subtracting scroll 4 and is moved or is out of shape owing to bearing rotatory force towards the direction deviating from gas compressor axle center when engine operation, thus, further increase and subtract the positional stability of scroll 4 and the reliability of work.
As the optimization of the arbitrary technological scheme of the utility model, retainer 6 also comprises support body portion 63 and joint 64, wherein:
Mounting hole 61 is arranged on joint 64, and the axial direction of mounting hole 61 is perpendicular with the axial direction subtracting scroll 4.
Support body portion 63 is fixedly connected with straight drum part 42, and the maximum bearing of trend in support body portion 63 is perpendicular with the axial direction subtracting scroll 4.
Joint 64 extends along the direction paralleled with the axial direction subtracting scroll 4 towards the direction close to intake section 41.
Defining flange 62 extends along the direction paralleled with the axial direction subtracting scroll 4 towards the direction close to exit portion 43.
Said structure is comparatively regular, simple, is convenient to processing, manufactures and assembling.
The gas compressor of the aeroengine that the utility model embodiment provides, comprising the first compressor disc 2 (is the compressor disc in left side in Fig. 3, be called for short left dish), the second compressor disc 5 (is the compressor disc on right side in Fig. 3, be called for short right dish), drum barrel 7 and the arbitrary technological scheme of at least one the utility model provide subtract scroll 4, wherein:
Drum barrel 7 is connected between the first compressor disc 2 and the second compressor disc 5.
First compressor disc 2 is installed with chamber, axle center deflection plate 3, drum barrel 7 is provided with drum barrel hole 70.
The intake section 41 subtracting scroll 4 is towards drum barrel hole 70, and the exit portion 43 subtracting scroll 4 is towards chamber, axle center deflection plate 3, and the air flow energy flowed out from the exit portion 43 subtracting scroll 4 to enter the chamber, axle center of gas compressor through chamber, axle center deflection plate 3.
Subtract scroll 4 to be fixedly connected with the first compressor disc 2 and/or the second compressor disc 5.
What the gas compressor of aeroengine was suitable for adopting the utility model to provide subtracts scroll 4 to reduce the flow losses of air-flow, improves the working efficiency of aeroengine, reduces its energy consumption.
Hereafter 1-Fig. 3 concentrates and sets forth optimal technical scheme of the present utility model by reference to the accompanying drawings:
The whole tubular type that the utility model provides subtracts whirlpool device bleed air system and rotates around running shaft 1, and sense of rotation as indicated by the arrows in fig. 3.End tapered expansion subtracts scroll 4 in the middle of the first compressor disc 2 i.e. left dish and the second compressor disc 5 of high-pressure compressor; Subtracting scroll 4 is arranged on retainer 6; Retainer 6 is fixedly connected with the snap ring on right dish 5 by bolt.The fraction of gas compressor mainstream channel enters between the first compressor disc 2 and the second compressor disc 5 by the drum barrel hole 7 on drum barrel, and radially flow to axis direction with the form of free vortex, gas flows to chamber, axle center with the form of forced vortex by subtracting scroll 4 subsequently, enter chamber, axle center by chamber, axle center deflection plate 3, thus realize centripetal air-entraining function.
Be made up of circumferential component velocity, radial velocity component, axial component velocity owing to subtracting spiral inlet place airspeed, and axial component velocity is much less than two other velocity component, substantially can not consider.In order to obtain the minimum pressure loss, when design point operating mode, the entry position subtracting scroll should obtain when the speed ratio of air-flow is 1, and namely now air-flow radially enters and subtracts scroll.But engine operating condition often changes in reality, so air-flow can not keep speed ratio to be 1 in the moment subtracting spiral inlet place, enter with certain angle to subtract scroll, now air-flow can impact and subtract on scroll inwall, form a little recirculating zone, hinder circulation area, reduce flow coefficient, increase local resistance loss.For this flow feature, the utility model will subtract spiral inlet section and intake section 41 is designed to cone expansion structure, as shown in Figure 1.Expansion angle a is about 15 °-30 ° according to design point operating mode, the size of intake section 41 on the axial direction subtracting scroll 4 (or be interpreted as: extending section height) h1 is about the 1/4-1/5 subtracting the total pipe range of scroll, ensure to subtract 2-3 times that spiral inlet area is section area in the middle part of pipe, now effectively can increase the circulation area of air-flow, reduce drag losses.
Gas flow direction engine rear flow is made in order to reduce bleed air-flow to the impact of engine shaft, subtracting scroll outlet port, air-flow need enter core chamber through deflection plate, due to spatial constraints, deflection plate is almost parallel to engine shaft, air-flow is forced to transfer to by Radial Flow through deflection plate and flows vertically, makes air-flow produce very large impact resistance loss.The design, for this flow feature, will subtract scroll outlet port and exit portion 43 is designed to expansion structure, and flow expansion is slowed down, and radial velocity is reduced, weakens the impact to deflection plate, thus the reduction pressure loss.Owing to subtracting the retainer of scroll near subtracting scroll outlet port, the size of exit portion 43 on the axial direction subtracting scroll 4 (or be interpreted as: extending section length) h2 is shorter, be about the 1/8-1/10 of pipe range, in order to make flow expansion abundant, angle of flare b should increase according to space size as far as possible, is about 30 °-45 °.In addition, during engine operation, because centrifugal action subtracts the trend that scroll has outside movement, the design of outlet cone expansion section can make to subtract scroll retainer and better retrain and subtract scroll, adds the reliability of system.
Above-mentioned arbitrary technological scheme disclosed in the utility model unless otherwise stated, if the number range of it discloses, so disclosed number range is preferred number range, anyly it should be appreciated by those skilled in the art: preferred number range is only the numerical value that in many enforceable numerical value, technique effect is obvious or representative.Because numerical value is more, cannot be exhaustive, so the utility model just discloses component values to illustrate the technical solution of the utility model, and the above-mentioned numerical value enumerated should not form restriction the utility model being created to protection domain.
If employ the word such as " first ", " second " herein to limit component, those skilled in the art should know: the use of " first ", " second " is only used to be convenient to describe carry out difference as not having outside Stated otherwise to component, the implication that above-mentioned word is not special.
Simultaneously, if above-mentioned the utility model discloses or relate to component or the structural member of connection fastened to each other, so, unless otherwise stated, be fixedly connected with and can be understood as: can releasably be fixedly connected with (such as using bolt or screw to connect), also can be understood as: to be non-removablely fixedly connected with (such as rivet, weld), certainly, connection fastened to each other also can be replaced by integral type structure (such as use casting technique is integrally formed create) (obviously cannot adopt except integrally formed technique).
In addition, apply in arbitrary technological scheme disclosed in above-mentioned the utility model for represent position relationship or shape term unless otherwise stated its implication comprise approximate with it, similar or close state or shape.Arbitrary parts that the utility model provides both can be assembled by multiple independent constituent element, and also can be one of the forming manufacture technics separate part out.
If employ term " " center " in description of the present utility model, " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", " outward " etc., orientation or the position relationship of so above-mentioned term instruction are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of instruction or hint indication subtract scroll or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
Finally should be noted that: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although be described in detail the utility model with reference to preferred embodiment, those of ordinary skill in the field have been to be understood that: still can modify to embodiment of the present utility model or carry out equivalent replacement to portion of techniques feature; And not departing from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technological scheme scope of the utility model request protection.
Claims (11)
1. subtract a scroll, it is characterized in that, comprise the intake section (41), straight drum part (42) and the exit portion (43) that are communicated with successively, wherein:
Described intake section (41), described straight drum part (42) and described exit portion (43) three are rotation body and the shaft axis of three coincides;
The inwall of described intake section (41) reduces gradually along entering flow path direction internal diameter size, and the inwall of described exit portion (43) increases gradually along going out flow path direction internal diameter size.
2. according to claim 1ly subtract scroll, it is characterized in that, the inwall of described intake section (41) and the inwall of described exit portion (43) are the conical surface.
3. according to claim 2ly subtract scroll, it is characterized in that, the inwall of described intake section (41) and the angle of described shaft axis are 15 ° ~ 30 °.
4. according to claim 2ly subtract scroll, it is characterized in that, described in described intake section (41) is of a size of on the described axial direction subtracting scroll, subtract 1/4 ~ 1/5 of the axial dimension of scroll.
5. according to claim 2ly subtract scroll, it is characterized in that, the inwall of described straight drum part (42) is consistent along its axial direction each section of cross-sectional dimension, and the area of the maximum cross section of the inwall of described intake section (41) is 2 ~ 3 times of the area of the cross section of the inwall of described straight drum part (42).
6. according to claim 2ly subtract scroll, it is characterized in that, the inwall of described exit portion (43) and the angle of described shaft axis are 30 ° ~ 45 °.
7. according to claim 2ly subtract scroll, it is characterized in that, described in described exit portion (43) is of a size of on the described axial direction subtracting scroll, subtract 1/8 ~ 1/10 of the axial dimension of scroll.
8. according to claim 1ly subtract scroll, it is characterized in that, the described scroll that subtracts also comprises retainer (6), described retainer (6) is fixedly connected with the outer wall of described straight drum part (42), and described retainer (6) is provided with mounting hole (61) and defining flange (62).
9. according to claim 8ly subtract scroll, it is characterized in that, the outer wall of described retainer (6) and described exit portion (43) abuts against close to the side of described intake section (41).
10. according to claim 8ly subtract scroll, it is characterized in that, described retainer (6) also comprises support body portion (63) and joint (64), wherein:
Described mounting hole (61) is arranged on described joint (64), and the axial direction of described mounting hole (61) and the described axial direction subtracting scroll perpendicular;
Described support body portion (63) is fixedly connected with described straight drum part (42), and the maximum bearing of trend in described support body portion (63) and described shaft axis perpendicular;
Described joint (64) extends along the direction paralleled with described shaft axis towards the direction close to described intake section (41);
Described defining flange (62) extends along the direction paralleled with described shaft axis towards the direction close to described exit portion (43).
The gas compressor of 11. 1 kinds of aeroengines, is characterized in that, comprises that the first compressor disc (2), the second compressor disc (5), drum barrel (7) and at least one claim 1-10 are arbitrary described subtracts scroll, wherein:
Described drum barrel (7) is connected between described first compressor disc (2) and described second compressor disc (5);
Described first compressor disc (2) is installed with chamber, axle center deflection plate, described drum barrel (7) is provided with drum barrel hole (70);
The described intake section (41) subtracting scroll is towards described drum barrel hole (70), the described exit portion (43) subtracting scroll is towards chamber, described axle center deflection plate, and the air flow energy flowed out from the described exit portion (43) subtracting scroll enters the chamber, axle center of described gas compressor through chamber, described axle center deflection plate;
The described scroll that subtracts is fixedly connected with described first compressor disc (2) and/or described second compressor disc (5).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520136114.9U CN204553354U (en) | 2015-03-11 | 2015-03-11 | Subtract the gas compressor of scroll and aeroengine |
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| CN201520136114.9U CN204553354U (en) | 2015-03-11 | 2015-03-11 | Subtract the gas compressor of scroll and aeroengine |
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| CN110005525A (en) * | 2019-03-01 | 2019-07-12 | 南京航空航天大学 | It is a kind of to go the compressor of whirl spraying mouth to subtract vortex structure with cascade-type |
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| CN108252955A (en) * | 2016-04-29 | 2018-07-06 | 中国航发常州兰翔机械有限责任公司 | Compressor tubular diffuser |
| CN108252955B (en) * | 2016-04-29 | 2023-09-08 | 中国航发常州兰翔机械有限责任公司 | Pipe diffuser for compressor |
| CN110005525A (en) * | 2019-03-01 | 2019-07-12 | 南京航空航天大学 | It is a kind of to go the compressor of whirl spraying mouth to subtract vortex structure with cascade-type |
| CN112129129A (en) * | 2020-09-24 | 2020-12-25 | 北京七星华创集成电路装备有限公司 | Heat exchange device and waste heat recovery equipment |
| CN114483219A (en) * | 2020-10-26 | 2022-05-13 | 中国航发商用航空发动机有限责任公司 | Vortex reducer, vortex reducing pipe and method for arranging vortex reducing pipe |
| CN114542640A (en) * | 2020-11-24 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Damping vibration attenuation device and aircraft engine |
| CN114542640B (en) * | 2020-11-24 | 2024-04-05 | 中国航发商用航空发动机有限责任公司 | Damping vibration attenuation device and aeroengine |
| CN114718910A (en) * | 2021-01-06 | 2022-07-08 | 中国航发商用航空发动机有限责任公司 | Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor |
| CN114961893A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Aeroengine vortex reducer air entraining device and aeroengine |
| CN114961893B (en) * | 2021-02-24 | 2023-08-04 | 中国航发商用航空发动机有限责任公司 | Air entraining device of vortex breaker of aero-engine and aero-engine |
| CN114810664A (en) * | 2022-04-26 | 2022-07-29 | 北京航空航天大学 | Variable-pipe-diameter vortex reducer for gas compressor and vortex reducing system thereof |
| CN114838000A (en) * | 2022-06-01 | 2022-08-02 | 北京航空航天大学 | Variable-length tubular type vortex reducer system of aero-engine compressor |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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