CN206785494U - Turbogenerator inlet casing - Google Patents
Turbogenerator inlet casing Download PDFInfo
- Publication number
- CN206785494U CN206785494U CN201720370787.XU CN201720370787U CN206785494U CN 206785494 U CN206785494 U CN 206785494U CN 201720370787 U CN201720370787 U CN 201720370787U CN 206785494 U CN206785494 U CN 206785494U
- Authority
- CN
- China
- Prior art keywords
- casing
- inlet
- procapsid
- axis
- inlet channel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Turbogenerator technical field is the utility model is related to, more particularly to a kind of turbogenerator inlet casing, including casing body, casing body has the axis hole that the axle for engine passes through；It is provided with inlet channel on casing body, the angle of the airintake direction of inlet channel and the axis of axis hole is acute angle, the axis of the outgassing direction of inlet channel parallel to axis hole.Turbogenerator inlet casing provided by the utility model, casing is provided with inlet channel, the airintake direction of inlet channel and the axial direction of engine shaft are at an acute angle, outgassing direction parallel to engine shaft axial direction, therefore the entrance of inlet channel will not by inlet casing Front Frame stop, so as to ensure air inflow, the air inlet of tilting simultaneously, air-flow has a velocity component on radial and axial, and for air-flow from import to during exit movement, air-flow pitot loss is smaller.
Description
Technical field
Turbogenerator technical field is the utility model is related to, more particularly to a kind of turbogenerator inlet casing.
Background technology
As turbogenerator air current composition process front end part, inlet casing runner design can be to the efficiency of compressor
Made a significant impact with performance.Rational inlet channel design should ensure that air-flow, and pitot loss is as small as possible in the channel, and
Air-flow should keep uniform in compressor blade entrance.
Traditional inlet casing is frequently with radial air inlet or axial admission.Radial air inlet casing can be liberated effectively into mechanism of qi
End spaces before casket, the turboshaft engine of inlet casing front end is arranged in suitable for decelerator, and such arrangement makes engine structure
It is compact, but air-flow is larger from being radially changed into axial movement generation air-flow pitot loss, influences compressor intake pressure.Axial admission
Casing can ensure that gas channel section is equal, and air-flow can keep stable at compressor inlet, but need to ensure when in use
Spacious before casing entrance, flow field will not be stopped by object and produce distortion, this allow for axial admission casing use range by
Limit.Particularly in some aircraft, the airintake direction of inlet casing is often axial direction, but can be flown in front of axial admission casing
Device other structures stop that air inflow is limited, and causes flow distortion big.And radial air inlet casing is because air inlet is perpendicular to axle
To air-flow does not have velocity component in radial direction, causes air-flow to be lost when entering casing larger.
Utility model content
Based on this, it is necessary to limited or the problems such as windage loss is larger for traditional inlet casing air inflow, there is provided
One kind can either effectively liberate end spaces before inlet casing, and and can enough ensures the less turbogenerator air inlet of air-flow pitot loss
Casing.
Above-mentioned purpose is achieved through the following technical solutions：
A kind of turbogenerator inlet casing, including casing body, casing body have the axle that the axle for engine passes through
Hole；
It is provided with inlet channel on casing body, the angle of the airintake direction of inlet channel and the axis of axis hole is acute angle,
Axis of the outgassing direction of inlet channel parallel to axis hole.
In one of the embodiments, the angular range of the axis of the airintake direction of inlet channel and axis hole be 40 °~
80°。
In one of the embodiments, the area of the air inlet of inlet channel is more than the area of the gas outlet of inlet channel.
In one of the embodiments, inlet channel be divided into being connected smoothly by air inlet to gas outlet three
Section, respectively first paragraph, second segment and the 3rd section；
Section of the first paragraph along the axis of axis hole is in gradually-reducing shape, and section of the second segment along the axis of axis hole is in arc-shaped, the
Three sections of sections along the axis of axis hole are in flat.
In one of the embodiments, the radius of the circular arc of second segment is 40mm~100mm.
In one of the embodiments, casing body includes casing procapsid and casing back casing, casing procapsid and machine
Casket back casing by it is some connection floors connect, between casing procapsid and casing back casing have interval, the interval formed into
Gas passage.
In one of the embodiments, multiple connection floors are circumferentially uniformly distributed around the axis of axis hole, and each connection
One end of floor is connected with casing procapsid, and the other end is connected with casing back casing.
In one of the embodiments, casing procapsid is in round table-like that casing back casing is in torus shape, and axis hole is arranged on
On casing procapsid, and the axis of axis hole overlaps with the longitudinal center line of casing procapsid；The longitudinal center line of casing back casing
Overlapped with the longitudinal center line of casing procapsid；The outside wall surface of casing procapsid is relative with casing back casing, casing back casing
Inner ring surface is relative with casing procapsid.
In one of the embodiments, the end face of the close casing back casing of casing procapsid and casing back casing are away from machine
The side of casket procapsid is concordant.
In one of the embodiments, in a ring, the outside wall surface of casing procapsid is interior with casing back casing for inlet channel
Anchor ring forms the two relative walls of inlet channel.
Above-mentioned turbogenerator inlet casing, casing are provided with inlet channel, the airintake direction and engine shaft of inlet channel
Axial direction it is at an acute angle, outgassing direction is parallel to the axial direction of engine shaft, therefore the entrance of inlet channel will not be by inlet casing
Front Frame stop, so as to ensure air inflow, while the air inlet of tilting, air-flow have speed on radial and axial
Component, for air-flow from import to during exit movement, air-flow pitot loss is smaller.
Brief description of the drawings
Fig. 1 is the structural representation for the turbogenerator inlet casing that the utility model embodiment provides；
Fig. 2 is view of the turbogenerator of the utility model embodiment offer from casing front case side；
Fig. 3 is Fig. 2 A-A sectional views；
Fig. 4 is the schematic diagram of Fig. 3 top half inlet channel；
Fig. 5 is the turbogenerator and the schematic diagram of air compressor structure assembling that the utility model embodiment provides.
Wherein：
100- casing bodies；
110- casing procapsids；
120- casing back casings；
130- connection floors；
140- axis holes；
200- inlet channels；
210- first paragraphs；
220- second segments；
The 3rd section of 230-；
300- axis；
400- compressors.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, by the following examples, and tie
Accompanying drawing is closed, turbogenerator inlet casing of the present utility model is further elaborated.It is it should be appreciated that described herein
Specific embodiment only explaining the utility model, be not used to limit the utility model.
It should be noted that when element is referred to as " being fixed on " another element, it can be directly on another element
Or there may also be element placed in the middle.When an element is considered as " connection " another element, it can be directly connected to
To another element or it may be simultaneously present centering elements.On the contrary, when element be referred to as " directly existing " another element " on " when,
In the absence of intermediary element.Term as used herein " vertically ", " horizontal ", "left", "right" and similar statement are
For illustrative purposes.
Turbogenerator inlet casing of the present utility model, is applicable to turboshaft engine or turbojet engine etc.,
Play a part of guiding air to enter compressor (including centrifugal-flow compressor and axial-flow compressor), there is effective solution to put into for it
End spaces before mechanism of qi casket, make engine structure compact, while ensure that air-flow pitot loss is smaller, make air-flow at compressor inlet
Kept for the advantages of stable.
As shown in figure 1, the turbogenerator inlet casing that the embodiment of the utility model one provides, including casing body 100,
Casing body 100 has the axis hole 140 that the axle for engine passes through；Inlet channel 200, air inlet are provided with casing body 100
The angle of the airintake direction of passage 200 and the axis 300 of axis hole 140 is acute angle, and the outgassing direction of inlet channel 200 is parallel to axle
The axis 300 in hole 140.
So that the turbogenerator inlet casing uses on board the aircraft as an example, the outlet of general turbogenerator inlet casing
Mouth is connected with the import of compressor, and the compressor 400 being connected with casing body 100 as shown in Figure 5 is centrifugal-flow compressor, but
The inlet casing may be equally applied to axial-flow compressor, for guiding air-flow to enter axial-flow compressor.Wherein, inlet casing
Air inlet angle designed according to aircraft cruising condition movement velocity, the axle of airintake direction and engine shaft needed for speed is bigger
To angle it is smaller.It is pointed out that carrying out CFD to airflow path, (Computational Fluid Dynamics- are calculated
Hydrodynamics) when calculating, in the selection of computational fields and Conductance calculation that general only selection inlet casing is calculated is different,
The motion state of aircraft air in flight is must take into consideration, the aircraft skin comprising engine should be included in computational fields,
It so can just obtain suitable inlet casing air inlet angle.
Referring to Fig. 2 and Fig. 3, as a kind of embodiment, the airintake direction of inlet channel 200 and the axis of axis hole 140
300 angular range is 40 °~80 °, such as the angle of the airintake direction of inlet channel 200 and axis 300 is in 75 °, and outlet
It is oriented parallel to axis 300.So, air-flow caused air-flow pitot loss in inlet channel 200 is smaller, and air-flow is exporting
Place is uniformly distributed, and ensures stabilization of the air-flow in the entrance of compressor 400.
Further, the area of the air inlet of inlet channel 200 is more than the area of the gas outlet of inlet channel 200, so
So that air-flow is compressed during being circulated in inlet channel 200, strengthen the pressure of exit air-flow.
Referring to Fig. 4, as a kind of embodiment, inlet channel 200 is divided into smoothed by air inlet to gas outlet
Cross connection three sections, respectively first paragraph 210, second segment 220 and the 3rd section 230；Axis 300 of the first paragraph 210 along axis hole 140
Section be in gradually-reducing shape, the section of axis 300 of the second segment 220 along axis hole 140 is in arc-shaped, and the 3rd section 230 along axis hole 140
The section of axis 300 is in flat.So, being connected smoothly makes flowing of the air-flow in inlet channel 200 more smooth, together
When to reduce air-flow pitot loss and reducing air-flow separation, runner turning arc radius should be as big as possible, it is preferred that second segment
The radius of 220 circular arc is 40mm~100mm.In addition, while Each part optimization is ensured, also need to shorten gas as far as possible
Circulate path total length, further to reduce the loss of air-flow stagnation pressure.
As a kind of embodiment, casing body 100 includes casing procapsid 110 and casing back casing 120, before casing
Housing 110 and casing back casing 120 are connected by some connection floors 130, casing procapsid 110 and casing back casing 120 it
Between have interval, the interval formed inlet channel 200.
Wherein, it is also 3,4 or 5 etc. to connect floor 130, axle of multiple connection floors 130 around axis hole 140
Line 300 is circumferential to be uniformly distributed, and one end of each connection floor 130 is connected with casing procapsid 110, the other end and casing rear shell
Body 120 is connected, and connection floor 130 is uniformly distributed, and the uniform of air-flow can be effectively ensured.
Further, casing procapsid 110 is in round table-like that casing back casing 120 is in torus shape, and axis hole 140 is arranged on
On casing procapsid 110, and the axis 300 of axis hole 140 overlaps with the longitudinal center line of casing procapsid 110；Casing back casing
120 longitudinal center line overlaps with the longitudinal center line of casing procapsid 110；After the outside wall surface and casing of casing procapsid 110
Housing 120 is relative, and the inner ring surface of casing back casing 120 is relative with casing procapsid 110.
Specifically, can be the small end of casing procapsid 110 from casing rear shell because casing procapsid 110 is in round table-like
In the ring of the side insertion casing back casing 120 of body 120, so that the outside wall surface of casing procapsid 110 and the phase of casing back casing 120
Right, the inner ring surface of casing back casing 120 is relative with casing procapsid 110, and casing procapsid 110 and casing back casing 120 it
Between it is spaced apart, the interval forms above-mentioned inlet channel 200.
It is connected for the ease of inlet casing body 100 with downstream configurations, such as compressor etc., casing procapsid 110 leans on
The end face (end face of i.e. foregoing small end) and side of the casing back casing 120 away from casing procapsid 110 of nearly casing back casing 120
Concordantly.In other embodiments, the end face of the small end of casing procapsid 110 and casing back casing 120 are away from casing procapsid 110
Side can not concordantly, wherein, end face and the casing back casing 120 for not representing the small end of casing procapsid 110 concordantly are remote
Certain distance be present between the side of casing procapsid 110.Referring to Fig. 1 structural representation, the front end face of casing procapsid 110
For large end face, rear end face is small end face, and the front end face of casing back casing 120 is behind the side of casing procapsid 110, casing
The rear end face of housing 120 is the side away from casing procapsid 110, then foregoing not concordant it may is that casing procapsid
110 small end face is more forward than the rear end face of casing back casing 120 or the small end face of casing procapsid 110 than casing after
The rear end face of housing 120 is rearward.In the small end face of casing procapsid 110 situation more forward than the rear end face of casing back casing 120
Under, the inlet channel 200 close to gas outlet can be by connection casing body 100 and the internal face structure of the connector of compressor 400
Into.Further, inlet channel 200 in a ring, the outside wall surface of casing procapsid 110 and the inner ring surface structure of casing back casing 120
Into the two relative walls of inlet channel 200.In other embodiments, inlet channel 200 can also be multiple independent passages,
It is circumferentially distributed between casing procapsid 110 and casing back casing 120 around axis 300.
Wherein, the air-flow of inlet channel 200 is oriented to mainly by the relative with casing back casing 120 of casing procapsid 110
Wall (i.e. the outside wall surface of casing procapsid 110) determine, therefore be to make the airintake direction of inlet channel 200 and axis hole 140
The angular range of axis 300 is 40 °~80 °, can be by the outside wall surface of the casing procapsid 110 at the airflow inlet of inlet channel 200
It is in 40 °~80 ° of inclined plane to be designed as with axis 300, and by the casing procapsid 110 of the air flow outlet of inlet channel 200
(arrow substantially represents airintake direction and the outflow of air-flow to the plane that outside wall surface is designed as parallel to axis 300 respectively in such as Fig. 3
Direction).And the relative wall (i.e. the inner ring surface of casing back casing 120) with casing procapsid 110 of casing back casing 120 can
To be designed as the ring surface parallel with the outside wall surface of casing procapsid 110.
In the present embodiment, in order to reach the effect of air-flow compression, outside wall surface and the casing back casing of casing procapsid 110
120 inner ring surface is not parallel all the time.Specifically, inlet channel 200 divides for first paragraph 210, second segment 220 and the 3rd section 230,
Because the section of axis 300 of the first paragraph 210 along axis hole 140 is in gradually-reducing shape, the first section that first paragraph 210 enters as air-flow, both
Play a part of guiding play a part of again air-flow compression, therefore, the outside wall surface of the casing procapsid 110 at first paragraph 210 with
The inner ring surface of casing back casing 120 is substantially at an acute angle, to form tapered effect.Axis 300 of the second segment 220 along axis hole 140
Section be in arc-shaped, be mainly used in connecting first paragraph 210 and the 3rd section 230, by relative to the oblique air-flow of axis 300 to
Guided parallel to the direction of axis 300, in the case where structure design allows, this section of arc radius should be as big as possible, mainly
The outside wall surface for designing casing procapsid 110 is larger in the radian of this section.3rd section of 230 section along the axis 300 of axis hole 140 is in
Flat, its main function are beneficial to steady air current, evenly into compressor 400, at the section, casing procapsid 110
The inner ring surface of outside wall surface and casing back casing 120 is to be parallel to each other, and each parallel to axis 300.In design process, machine need to be ensured
The outside wall surface of casket procapsid 110 and the inner ring surface of casing back casing 120 are smooth face, to ensure the smooth outflow of air-flow.
The turbogenerator inlet casing that the utility model embodiment provides, its inlet channel have that pitot loss is smaller,
The advantages of channel outlet air-flow is uniformly distributed, and due to the intake method of diagonal flow type so that inlet casing structure relative compact, enter
Gas is not influenceed by inlet casing front-end architecture, is easy to arrange have a wide range of application in whirlpool axle and turbojet engine.
Each technical characteristic of embodiment described above can be combined arbitrarily, to make description succinct, not to above-mentioned reality
Apply all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, the scope that this specification is recorded all is considered to be.
Embodiment described above only expresses several embodiments of the present utility model, and its description is more specific and detailed,
But therefore it can not be interpreted as the limitation to utility model patent scope.It should be pointed out that the common skill for this area
For art personnel, without departing from the concept of the premise utility, various modifications and improvements can be made, these are belonged to
The scope of protection of the utility model.Therefore, the protection domain of the utility model patent should be determined by the appended claims.
Claims (10)
1. a kind of turbogenerator inlet casing, it is characterised in that including casing body, the casing body, which has, supplies engine
The axis hole that passes through of axle；
Inlet channel, the angle of the airintake direction of the inlet channel and the axis of the axis hole are provided with the casing body
For acute angle, the axis of the outgassing direction of the inlet channel parallel to the axis hole.
2. turbogenerator inlet casing according to claim 1, it is characterised in that the airintake direction of the inlet channel
Angular range with the axis of the axis hole is 40 °~80 °.
3. turbogenerator inlet casing according to claim 1, it is characterised in that the air inlet of the inlet channel
Area is more than the area of the gas outlet of the inlet channel.
4. turbogenerator inlet casing according to claim 1, it is characterised in that the inlet channel is by the air inlet
Mouthful be divided into being connected smoothly to the gas outlet three sections, respectively first paragraph, second segment and the 3rd section；
The section of axis of the first paragraph along the axis hole is in gradually-reducing shape, the section of axis of the second segment along the axis hole
In arc-shaped, the 3rd section of section along the axis of the axis hole is in flat.
5. turbogenerator inlet casing according to claim 4, it is characterised in that the radius of the circular arc of the second segment
For 40mm~100mm.
6. according to the turbogenerator inlet casing described in claim any one of 1-5, it is characterised in that the casing body bag
Casing procapsid and casing back casing are included, the casing procapsid is connected with the casing back casing by some connection floors,
There is interval, the interval forms the inlet channel between the casing procapsid and the casing back casing.
7. turbogenerator inlet casing according to claim 6, it is characterised in that multiple connection floors are around institute
The axis for stating axis hole is circumferentially uniformly distributed, and one end of each connection floor is connected with the casing procapsid, the other end
It is connected with the casing back casing.
8. turbogenerator inlet casing according to claim 6, it is characterised in that the casing procapsid is in round platform
Shape, the casing back casing are in torus shape, and the axis hole is arranged on the casing procapsid, and the axis of the axis hole with
The longitudinal center line of the casing procapsid overlaps；The axle of the longitudinal center line of the casing back casing and the casing procapsid
Overlapped to center line；
The outside wall surface of the casing procapsid is relative with the casing back casing, inner ring surface and the machine of the casing back casing
Casket procapsid is relative.
9. turbogenerator inlet casing according to claim 8, it is characterised in that the close institute of the casing procapsid
The end face for stating casing back casing is concordant with side of the casing back casing away from the casing procapsid.
10. turbogenerator inlet casing according to claim 8, it is characterised in that the inlet channel in a ring, institute
State the two relative walls that the outside wall surface of casing procapsid forms the inlet channel with the inner ring surface of the casing back casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720370787.XU CN206785494U (en) | 2017-04-10 | 2017-04-10 | Turbogenerator inlet casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720370787.XU CN206785494U (en) | 2017-04-10 | 2017-04-10 | Turbogenerator inlet casing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206785494U true CN206785494U (en) | 2017-12-22 |
Family
ID=60706024
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720370787.XU Active CN206785494U (en) | 2017-04-10 | 2017-04-10 | Turbogenerator inlet casing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206785494U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109374207A (en) * | 2018-12-12 | 2019-02-22 | 合肥动联自动化科技有限公司 | Air-guide disk is used in a kind of test of turbocharger |
| CN109667669A (en) * | 2018-12-28 | 2019-04-23 | 中国科学院工程热物理研究所 | Gas turbine inlet air casing |
-
2017
- 2017-04-10 CN CN201720370787.XU patent/CN206785494U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109374207A (en) * | 2018-12-12 | 2019-02-22 | 合肥动联自动化科技有限公司 | Air-guide disk is used in a kind of test of turbocharger |
| CN109667669A (en) * | 2018-12-28 | 2019-04-23 | 中国科学院工程热物理研究所 | Gas turbine inlet air casing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105484871B (en) | Vehicle-mounted gas turbine transformed from obsolete fanjet | |
| US9157396B2 (en) | Nozzled turbine | |
| CN102536913B (en) | Bearing cooling in air cycle machine controls | |
| CN103867235B (en) | A kind of tubular type subtracts whirlpool device bleed air system | |
| RU2563297C2 (en) | Nacelle of jet-turbine engine | |
| UA93364C2 (en) | Turbomachine comprising a system for cooling the downstream face of an impeller of a centrifugal compressor | |
| US10240612B2 (en) | Centrifugal compressor with inlet duct having swirl generators | |
| CN206785494U (en) | Turbogenerator inlet casing | |
| JPH07500399A (en) | Improved cooling fluid ejector | |
| KR20050000319A (en) | Turbocharger | |
| CN104564166B (en) | The axial turbine impeller of leading edge with bending | |
| CN207363711U (en) | Cooling circuit and corresponding turbine device and turbomachinery for multi wall blade | |
| CN112576366B (en) | Two-wheeled pressure turbine cooler driven by air dynamic pressure bearing | |
| JP2017122449A (en) | Systems and methods for compressor diffusion slot | |
| CN106870465A (en) | A kind of compressor, gas turbine and compressor stability-enhancement synergistic method | |
| US11248483B2 (en) | Turbine housing and method of improving efficiency of a radial/mixed flow turbine | |
| CN107504066A (en) | A kind of integral shaft symmetrical jet pressure stabilizing cavity supplied to high pressure disk gas bearing | |
| CN207568949U (en) | Subtract whirlpool device air entraining device and aero-engine | |
| US10196902B2 (en) | Cooling for gas turbine engine components | |
| CN102589837A (en) | Large fluid pressure wind tunnel | |
| CN107630725A (en) | Suitable for testing the air inlet volute of ride | |
| CN103016077B (en) | Turbine disk cooling and packing device | |
| Herrick | Effects of inlet distortion on aeromechanical stability of a forward-swept high-speed fan | |
| CN110374928A (en) | The design method and tubular diffuser of tubular diffuser | |
| CN205277627U (en) | Miniature turbofan engine divides division exhaust apparatus with rectifier |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |