CN207333296U - Gas-turbine unit - Google Patents

Abstract

The utility model provides a kind of gas-turbine unit, including interior casing, compressor and auxiliary air air collecting chamber, which includes stator and rotor, and the outer wall of the interior casing is equipped with the bleed ports for including multiple air flues of perforation；For each air flue relative to the inclined main axes of the gas-turbine unit, which deviates from the main shaft；The entrance of each air flue is bent to the opposite direction of the direction of rotation of the rotor in the circumferential, and the outlet of each air flue is bent from the entrance of the air flue to the direction of rotation of the rotor；The circumferential direction is perpendicular to the direction of the main shaft of the gas-turbine unit.The utility model proposes gas-turbine unit the axially and tangentially kinetic energy of these gases can be preferably recycled when gas is drawn from bleed ports, there is higher whole efficiency.

Description

Gas-turbine unit

Technical field

It the utility model is related to a kind of gas-turbine unit, more particularly to one kind energy when gas is drawn from bleed ports The gas-turbine unit of the enough kinetic energy for preferably recycling these gases.

Background technology

Bleed is in various types of axial flow compressors using very extensive.Such as in aviation axial flow compressor, in order to Reach the purpose of turbine cooling, compressor anti-asthma, boundary layer suction, often opened on interior casing one or more hole or Groove, mainstream is drawn by gas.The gas being brought out can enter secondary ventilation system, be directly discharged into air or re-inject into Swim sprue.However, realize that bleed can bring problems with simply by the mode of perforate or fluting：

From mainstream flow to bleed ports gas its axially and tangentially speed is all considerable, therefore with the two directions Kinetic energy.When gas pours bleed ports, flow direction suddenly change so that the kinetic energy in the two directions is substantially lost. When being adjustable vane particularly in front of bleed ports, this problem is even more serious.Because sometimes for adjustable vane rotation angle It is larger so that outlet flow angle deviates axial more.At this moment the tangential kinetic energy of bleed stream is with regard to bigger.If this portion cannot be utilized The energy divided, loss will become than more significant.On the other hand, in the axial flow compressor of some gas turbines, bleed ports can To be arranged on the downstream of rotor.Compared with the bleed ports in stator downstream are arranged in aero-engine, set in gas turbine Bleed ports in rotor downstream can cause tangential kinetic energy of the air-flow with bigger for flowing into bleed ports.If therefore cannot be by this portion Energy is divided properly to utilize, then the energy loss brought will bigger.

In addition, gas direction suddenly change when flowing into bleed ports, causes not only to give there are strong vortex in bleed ports Auxiliary air flow path brings crushing, can also influence the flow field of main flow area, deteriorates Capability of Compressor.

It is therefore desirable to provide a kind of axial direction that these gases can be preferably recycled when gas is drawn from bleed ports With the gas-turbine unit of tangential kinetic energy.

Utility model content

The purpose of this utility model is to provide one kind can preferably recycle these gas when gas is drawn from bleed ports The gas-turbine unit of the axially and tangentially kinetic energy of body.

The utility model provides a kind of gas-turbine unit, including interior casing, compressor and auxiliary air air collecting chamber, should Compressor includes stator and rotor, which is attached at the outer wall of the interior casing, is set on the outer wall of the interior casing There are the bleed ports inside the perforation interior casing and inside the auxiliary air air collecting chamber；The bleed ports include multiple air flues, multiple to be somebody's turn to do Outer wall of the air flue circumferential array in interior casing；Each air flue is relative to the inclined main axes of the gas-turbine unit, the inclination Direction is from the air inlet side of the gas-turbine unit to exhaust side, away from the main shaft；The entrance of each air flue is in the combustion gas In the circumferential direction of turbogenerator, bent to the opposite direction of the direction of rotation of the rotor, the outlet of each air flue is in the combustion gas whirlpool In the circumferential direction of turbine, from the entrance of the air flue, bent to the direction of rotation of the rotor；The circumferential direction is perpendicular to the combustion gas whirlpool The direction of the main shaft of turbine.

At least one embodiment according to the present utility model, the air flue are the slots on the outer wall of the interior casing.

At least one embodiment according to the present utility model, the edge of the entrance and exit of the slot is all fillet.

At least one embodiment according to the present utility model, is equipped with multiple bleed blades in the bleed ports, adjacent two The air flue is formed between bleed blade.

At least one embodiment according to the present utility model, the bleed blade have shape factor N=b/ (d-t), wherein b For the chord length of the bleed blade, t is the maximum gauge of the bleed blade, and d is the pitch of the bleed blade；Shape factor N's The upper limit is 1.2 or 1.5 or 1.8；The lower limit of shape factor N is 0.5 or 0.6 or 0.8.

At least one embodiment according to the present utility model, the upper limit of the maximum gauge t of the bleed blade be 1.2 millimeters or 1.5 millimeters or 2 millimeters.

At least one embodiment according to the present utility model, the maximum gauge t of the bleed blade and the string of the bleed blade The scope of the ratio of long b is 0.05 to 0.3.

At least one embodiment according to the present utility model, the leading edge and/or trailing edge of the bleed blade are fillet.

At least one embodiment according to the present utility model, the interior casing include the upstream wall positioned at the bleed ports upstream With the downstream wall positioned at the bleed ports downstream；

The bleed blade is fixedly connected with the upstream wall and/or the bleed blade is fixedly connected with the downstream wall.

At least one embodiment according to the present utility model, interior casing include positioned at the bleed ports upstream upstream wall and Downstream wall positioned at the bleed ports downstream, the upstream wall and the downstream wall are structure as a whole.

At least one embodiment according to the present utility model, the entrance of the air flue and the upper limit of the circumferential angle are 15 degree Or 20 degree or 25 degree, the entrance of the air flue and the lower limit of the circumferential angle are 50 degree or 60 degree or 70 degree.

At least one embodiment according to the present utility model, the outlet of the air flue and the upper limit of the circumferential angle are 95 degree Or 100 degree or 110 degree, the entrance of the air flue and the lower limit of the circumferential angle are 75 degree or 80 degree or 85 degree.

At least one embodiment according to the present utility model, the gas-turbine unit are aero-engines, the bleed ports Set the downstream of the blade of the stator of the compressor, the rotor blade upstream.

At least one embodiment according to the present utility model, the gas-turbine unit are gas turbines, which sets Put the downstream of the blade of the rotor of the compressor, the stator blade upstream.

At least one embodiment according to the present utility model, the compressor are axial-flow compressors.

The utility model proposes gas-turbine unit, due to use new bleed structure, thus by gas from Bleed ports can preferably recycle the axially and tangentially kinetic energy of these gases when drawing, have higher whole efficiency.

It should be appreciated that general description and the following detailed description more than the utility model is all exemplary and illustrative , and it is nonrestrictive.These are described in detail it is intended that the utility model being somebody's turn to do such as claim provides further explanation.

Brief description of the drawings

It is that the utility model is further understood to provide including attached drawing, they are included and form the one of the application Part, attached drawing show the embodiment of the utility model, and the work for explaining the utility model principle is played together with this specification With.In attached drawing：

Fig. 1 shows the axial section knot of the subregion of one embodiment of the gas-turbine unit of the utility model Structure schematic diagram；

Fig. 2 shows the bleed ports and its neighboring area of one embodiment of the gas-turbine unit of the utility model Axial section structure diagram；

Fig. 3 shows the structure diagram of the bleed ports of one embodiment of the gas-turbine unit of the utility model；

Fig. 4 a show that the cross-section structure of the bleed ports of one embodiment of the gas-turbine unit of the utility model shows It is intended to；

Fig. 4 b show that the cross-section structure of the bleed ports of one embodiment of the gas-turbine unit of the utility model shows It is intended to；

Fig. 5 a show the cross-section structure of the bleed ports of another embodiment of the gas-turbine unit of the utility model Schematic diagram；

Fig. 5 b show the cross-section structure of the bleed ports of another embodiment of the gas-turbine unit of the utility model Schematic diagram；

Fig. 6 a show the bleed ports of one embodiment of the gas-turbine unit of the utility model and cuing open for interior casing Face structure diagram；

Fig. 6 b show the bleed ports of another embodiment of the gas-turbine unit of the utility model and interior casing Cross-sectional view；

Fig. 6 c show the bleed ports of another embodiment of the gas-turbine unit of the utility model and interior casing Cross-sectional view；

Fig. 7 shows the performance chart of the bleed ports of the utility model and the bleed ports of the prior art.

Embodiment

The embodiment of the utility model is described with detailed reference to attached drawing now.Now with detailed reference to the utility model Preferred embodiment, its example are shown in the drawings.In the case of any possible, identical mark will be used in all of the figs To represent the same or similar part.In addition, although the term used in the utility model is from public term Selection, but some terms mentioned in the utility model specification are probably applicant to be selected by his or her judgement , its detailed meanings illustrates in the relevant portion of description herein.In addition, it is desirable to not only by used actual art Language, and the meaning that is also to be contained by each term understands the utility model.

Illustrate the structure of an optional embodiment of the utility model with reference first to Fig. 1.As shown in Figure 1, according to one A nonrestrictive example, the gas-turbine unit of the utility model include interior casing 1, compressor 2 and auxiliary air gas collection Chamber 3.Wherein compressor 2 includes rotor 20.Auxiliary air air collecting chamber 3 is arranged on outside the outer wall of interior casing 1 and is close to interior casing 1 Outer wall.The specific set-up mode of auxiliary air air collecting chamber 3 can be various.One way in which be it is as shown in Figure 1, it is secondary Air air collecting chamber 3 is using a part of outer wall of interior casing 1 as the side wall of itself.Other modes can also be auxiliary air gas collection Chamber 3 has itself independent outer wall, and a part for the outer wall is close to the outer wall of interior casing 1.

With reference to figure 1-2, the outer wall of interior casing 1 is equipped with the inside of casing 1 and drawing inside auxiliary air air collecting chamber 3 in perforation Gas port 11.Bleed ports 11 enable the gas inside interior casing 1 to enter by bleed ports 11 in auxiliary air air collecting chamber 3 Portion.With reference to figure 3, bleed ports 11 include multiple air flues 12.Outer wall of multiple air flue circumferential arrays in interior casing 1.It is new in this practicality In type, the major axes orientation (i.e. the direction of X-axis in Fig. 1) of gas-turbine unit is defined as axial direction.Also, it will be perpendicular to combustion gas The plane of the major axes orientation (i.e. the direction of X-axis in Fig. 1) of turbogenerator intersects the circular direction to be formed with interior casing 1 determines Justice is " circumferential direction ".

With reference to figure 2, each the air flue is (i.e. opposite relative to the inclined main axes of the gas-turbine unit for each air flue 12 The direction of X-axis in Fig. 1, axial).Specific incline direction is, from the air inlet side of the gas-turbine unit (in Fig. 2 Left side) to exhaust side (in Fig. 2 right side) deviate from the main shaft.In other words, on the axis projection of the gas-turbine unit, often For the entrance 121 of a air flue 12 closer to the main shaft of the gas-turbine unit, the outlet 122 of each air flue 12 more deviates from should The main shaft of gas-turbine unit.For from effect, when each air flue 12 is so that air-flow flows in air flue 12, increasingly To the main shaft away from gas-turbine unit.The reason for so setting is that the gas inside interior casing 1 is all with higher speed Move and (i.e. moved in the X-axis direction in Fig. 1) from air admission hole to exhaust outlet vertically, be arranged to meet to gas by air flue 12 in the axial direction The gas that stream is conducive to inside interior casing 1 is more swimmingly exported through each air flue 12.

With reference to figure 3, in the circumferential, the entrance 121 of each air flue 12 is to the direction of rotation (direction of rotation of rotor of rotor 20 Opposite direction bending as indicated by the arrows in fig. 3), that is, meet the direction of rotation to rotor 20.Since the gas inside interior casing 1 exists Under the drive of rotor 20, there is certain circumferential speed, the entrance 121 of air flue 12 is arranged to meet to air-flow is conducive to interior machine Gas inside casket 1 is more swimmingly imported in air flue 12.On the other side, the outlet 122 of air flue 12 is compared to entrance 121 not So meet to air-flow.That is, relative to the entrance 121 of air flue 12, the outlet 122 of air flue 12 is from the entrance 121 of the air flue, to rotor 20 direction of rotation bending.In other words, in the radially projecting of the gas-turbine unit, the entrance 121 of each air flue 12 is met To the direction of rotation of rotor.Relative to the entrance 121 of air flue 12, each outlet 122 is closer to the gas-turbine unit The direction (radial direction) of diameter.It is such to set so that 12 integrally bending of air flue, and meet in the circumferential to air-flow angle increasingly It is small, air-flow along each air flue 12 flow when, its flow to gradates for be directed toward auxiliary air air collecting chamber 3.Such structure makes In gas inside casing 1 tangential kinetic energy by transfer pressure energy to greatest extent, significantly reduce cutting for bleed gas To dynamic loss of energy.In addition, such setting can also reduce the vortex of bleed ports 11 at the same time.

It is worth noting that, one of the gas-turbine unit that the example of the above simply proposes the utility model can The explanation of the example of choosing.The mass part for the gas-turbine unit that the utility model is proposed can be provided with diversified Set-up mode.For example, can be by the interface of the 11 auxiliary air air collecting chamber 3 of interface and bleed ports of bleed ports 11 and interior casing 1 all What is set is more round and smooth, so that flowing through bleed ports 11 flows more smooth, energy loss smaller.It is non-limiting with some below Example the change of at least a portion of the utility model is further detailed.

First, air flue 12 can be made in many ways.With reference to figure 4a, according to a nonrestrictive example, air flue 12 It is the slot on the outer wall of interior casing 1.Such setting can make it that the comparison of air flue 12 is simple and cause interior casing 1 Integral strength it is preferable.Optionally, in current non-limitative example, the edge of the entrance and exit of slot is all fillet. That is tetra- regions of A, B, C, D in Fig. 4 are all fillets.Such setting enables to flow through the air-flow of bleed ports 11 and interior casing The flowing of gas in 1 is more smooth.

On the other hand, the slot that bleed ports 11 may not be on the outer wall by interior casing 1 forms, but with others Structure.With reference to figure 5a, according to a nonrestrictive example, the continuous opening equipped with multiple bleed blades 13 in one. In current non-limitative example, air flue 12 is formed between adjacent two bleed blades 13.It is such to set compared to using slot The advantages of putting mainly includes two aspects.On the one hand, such setting can relatively easily control the size of bleed blade 13 And form.On the other hand, it is such to set it is also possible that the thickness of bleed blade be thinner, so as to play reduction air flue 12 Between spacing, and reduce vortex etc. undesirable sinuous flow effect.

The concrete form of bleed blade 13 also has highly important influence for overall drainage effect, therefore use has The bleed blade 13 of right dimensions and shapes is highly important.With continued reference to Fig. 5 a, according to a nonrestrictive example, The form of bleed blade 13 can be configured to meet certain shape factor scope.Specifically, the chord length according to bleed blade B, the maximum gauge t of bleed blade and the pitch d of bleed blade can calculate the shape factor N, wherein N=of bleed blade 13 b/(d-t).When the shape factor N of bleed blade 13 is in the range of 0.5-1.8, there can be preferable drainage effect. In the range of this, shape factor N can be adjusted as needed.

Specifically, shape factor is bigger, stronger to the ability of turning back of air-flow, but resistance can also increase therewith.Particularly Blade wake passing loss is the direct ratio increase with increasing for the number of blade.So the selection of shape factor is turned back energy in air-flow The result compromised between power and loss.When tap air channel can be made long, blade can also be done long.Use at this time The less number of blade can reach higher shape factor, and will not bring very big Trailing Edge Loss.At this moment shape factor is just It can take larger, such as bleed blade 13 is set to have 1.2 or 1.5 larger shape factor N.Conversely, work as bleed When passage is shorter, to reach same bleed effect, the required number of blade is more.At this moment Trailing Edge Loss can be bigger, so At this moment shape factor just should be obtained suitably a little bit smaller.Such as bleed blade 13 is set to the form with less 0.6 or 0.8 Coefficient N.Certainly, the shape factor of bleed blade 13 is set, it is also many other in addition to needing to consider the length of tap air channel Factor need to consider.These factors include air velocity direction, gasflow mach number and bleed flow etc..Therefore above-mentioned two Example is simply to illustrate that can be by adjusting the shape factor of bleed blade 13 to adapt to have each of different operating modes and parameter Kind gas-turbine unit.

With continued reference to Fig. 5 a, except through setting outside the shape factor of bleed blade 13, the maximum gauge t of bleed blade 13 Setting can also large effect drainage overall effect.On the one hand, excessively thin bleed blade 13 can cause bleed blade 13 Structural strength deficiency, so as to reduce the life and reliability of gas-turbine unit.On the other hand, blocked up 13 meeting of bleed blade Thicker tail is produced, so as to destroy the order of bleed air-flow.Therefore generally by the upper limit of the maximum gauge t of bleed blade 13 It is arranged between 1.2 millimeters to 2 millimeters, such as a typical aero-turbine can be configured with maximum gauge as 1.5 The bleed blade 13 of millimeter.

Pressure transformation efficiency of the ratio relation of the maximum gauge t of the bleed blade 13 and chord length b of bleed blade to bleed And resistance.Therefore the ratio of suitable maximum gauge t and the chord length b of bleed blade should be selected.The inventor of the utility model Found by extremely multiple repetition test, the maximum gauge t of bleed blade 13 and the ratio of the chord length b of bleed blade are arranged on When in the range of 0.05 to 0.3, preferable bleed effect can be obtained.

Except the size and form of bleed blade 13, the shape of itself of bleed blade 13 can also influence the pressure conversion of bleed Efficiency and resistance.In a nonrestrictive example of the utility model, in leading edge and trailing edge that bleed blade 13 has At least one is rounded shapes.Such setting can reduce the eddy resistance of bleed blade 13.

Include with reference to figure 6a-6c, interior casing 1 positioned at the upstream wall 100 of bleed ports upstream and positioned at bleed ports downstream Downstream wall 200.Upstream wall 100 and downstream wall 200 can both take split structure, can also use integral type knot Structure.For the interior casing using integral structure, with reference to figure 6a, when making the air flue 12 of bleed ports 11, can take pre- If position makes the method for multiple slots.It is on the other side, with reference to figure 6b and 6c, for using split type 100 He of upstream wall The interior casing 1 that downstream wall 200 is formed, then can form air flue 12 using bleed blade 13.Bleed blade 13 can both be adopted Being first fabricated separately as shown in Figure 6b is taken, can also in the bleed ports 11 that the method fixed afterwards with upstream wall 100 is fixed on Using being first fabricated separately as shown in the figure 6c, the method fixed afterwards with downstream wall 200 is fixed in bleed ports 11.It is worth note Meaning, bleed blade 13 is fixed with upstream wall 100 not to be represented and cannot be fixed with downstream wall 200, and vice versa.Change speech It, bleed blade 13 both can be only fixed with one of upstream wall 100 and downstream wall 200, can also be with upstream wall 100th, downstream wall 200 is all fixedly connected.

With reference to figure 4b, 5b, the angle between the entrance of air flue 12 and the circumferential direction of the gas-turbine unit should not be too large It is unsuitable too small.When either forming air flue 12 using bleed blade 13, the angle α 1 of the entrance of air flue 12, or made using slot For air flue 12 when, the angle β 1 of the entrance of air flue 12 should be moderate.Generally this angle is arranged between 15-70 degree.Folder The specific size at angle, should according to bleed flow, bleed ports upstream main flow area air velocity direction depending on so that the import of air flue Flow direction when angle enters bleed ports with gas coincide substantially.Angle is too big or too small can all increase loss.Work as bleed Flow is larger and when the tangential flow velocity of mainstream is smaller, can use larger 1/ β 1 (such as 50 degree or 60 degree) of α；It is on the contrary then can be with Using less 1/ β 1 (such as 20 degree or 25 degree) of α.

It is similar with the angle of the entrance of air flue 12 with continued reference to Fig. 4 b, 5b, outlet and circumferential 2/ β of angle α of air flue 12 2 also should not be too large or unsuitable too small.Excessive 2/ β 2 of angle α can cause bleed air-flow to produce reverse flow, so as to cause energy Loss.And too small angle can cause tangential (circumferential direction) kinetic energy of gas to be most preferably converted into pressure.Therefore, generally will The entrance of air flue 12 and the angle of circumferential direction are set as between 75-110 degree.Setting more than 90 degree (i.e. with 20 direction of rotation of rotor Conversely) it is the reason for 2/ β 2 of angle α, airflow direction has certain hysteresis quality by the adjustment of air flue 12.Therefore set more than 90 2/ β 2 (such as 2/ β 2 of angle α is arranged to 95,100 degree) of angle α of degree enables to the air-flow of drainage to be preferably adjusted to Towards auxiliary air air collecting chamber 3.However, such setting can cause overall resistance increase of the air-flow in air flue 12.Therefore it is So that the air-flow velocity more block in air flue 12, drainage efficiency higher, 90 degree of angle α 2/ β 2 can be also set lower than.For example, can 2/ β 2 of angle α is arranged to less 75 degree, 80 degree or 85 degree.

It is worth noting that, " gas-turbine unit " word of the utility model should be interpreted broadly, either The aero-engine of aviation gas turbine jet engine, aviation gas turbine Duct-Burning Turbofan etc, can also other forms Engine.For example, marine gas turbine, automotive gas turbines, industrial gas turbine etc..Above-mentioned bleed structure can expire Utilization of the gas-turbine unit of sufficient the utility model in every field.However, aero-engine and gas turbine are due to fortune It is different with occasion, often there is different designs for compressor.The bleed structure of the utility model, can also be directed to different Gas-turbine unit, using different settings.First, aero-engine and gas turbine all have stator and rotor.With Fig. 1 In gas-turbine unit exemplified by, which has multiple rotor bleed blades 21 and multiple stator bleeds Blade 22.The purpose of bleed is primarily to secondary ventilation system uses rather than for anti-asthma between aero-engine progress level.Will Bleed ports are arranged on after rotor, since the tangential kinetic energy of bleed stream is larger, so the loss of energy can be caused larger.So work as During as aero-engine, bleed ports 11 can be set to downstream, the rotor bleed blade of the stator bleed blade 22 of compressor 21 upstream.

Compared with aero-engine, the adjustable vane of gas turbine is far from more as aero-engine.For example, certain is worked as For horizontal aero-engine, there is 5 row's adjustable vanes, but the gas turbine that another major parameter is similar in 10 grades of compressors In, 15 grades of compressors are configured, wherein only 3 row's adjustable vanes.Therefore, in order to stable in liter Rotation Process, it is necessary to Extract more air out between level, and a big chunk anti-asthma responsibility is undertaken by bleed between level.So work as the utility model Gas-turbine unit as gas turbine when, bleed ports 11 can be arranged under the rotor bleed blade 21 of compressor Trip, the upstream of the stator bleed blade 22.It is such to set so that gas-turbine unit is with larger bleed ratio While (more much greater than aero-engine), it can still avoid due to rotor rotating stall caused by bleed.

Optionally, the bleed structure of the utility model is suitable for equipment in the gas-turbine unit with axial-flow compressor On.

Understood with reference to figure 7, relative to the pressure curve Y of traditional prismatic blade, using bleed structure provided by the utility model Afterwards, the entire lowering amplitude of pressure curve X of the gas in air entraining passage is smaller.This just illustrates that the utility model no longer has meeting The structure that the amount of allowing gas to drastically reduces, bleed structure provided by the utility model can be maintained preferably into bleed structure Air-flow pressure, so as to fulfill reduce energy loss purpose.

Although the utility model is described with reference to current specific embodiment, ordinary skill in the art Personnel are it should be appreciated that the embodiment of the above is intended merely to explanation the utility model, without departing from the utility model spirit In the case of can also make various equivalent change or replacement, therefore, as long as to upper in the spirit of the utility model State the change of embodiment, modification will all fall in the range of following claims.

Claims (15)

1. a kind of gas-turbine unit, including interior casing, compressor and auxiliary air air collecting chamber, the compressor include stator And rotor, the auxiliary air air collecting chamber are attached at the outer wall of the interior casing, the outer wall of the interior casing is equipped with perforation institute State the bleed ports inside interior casing and inside the auxiliary air air collecting chamber；

The bleed ports include multiple air flues, outer wall of multiple air flue circumferential arrays in interior casing；

For each air flue relative to the inclined main axes of the gas-turbine unit, the incline direction is from the combustion gas whirlpool The air inlet side of turbine is to exhaust side, away from the main shaft；

The entrance of each air flue is in the circumferential direction of the gas-turbine unit, to the negative side of the direction of rotation of the rotor To bending, the outlet of each air flue is in the circumferential direction of the gas-turbine unit, from the entrance of the air flue, to described turn The direction of rotation bending of son；

The circumferential direction is perpendicular to the direction of the main shaft of the gas-turbine unit.

2. gas-turbine unit according to claim 1, it is characterised in that：The air flue is the outer wall of the interior casing On slot.

3. gas-turbine unit according to claim 2, it is characterised in that：The edge of the entrance and exit of the slot All it is fillet.

4. gas-turbine unit according to claim 1, it is characterised in that：Multiple bleed leaves are equipped with the bleed ports Piece, forms the air flue between adjacent two bleed blades.

5. gas-turbine unit according to claim 4, it is characterised in that：The bleed blade has shape factor N =b/ (d-t), wherein b are the chord length of the bleed blade, and t is the maximum gauge of the bleed blade, and d is the bleed blade Pitch；

The upper limit of the shape factor N is 1.2 or 1.5 or 1.8；

The lower limit of the shape factor N is 0.5 or 0.6 or 0.8.

6. gas-turbine unit according to claim 4, it is characterised in that：The maximum gauge t's of the bleed blade The upper limit is 1.2 millimeters or 1.5 millimeters or 2 millimeters.

7. gas-turbine unit according to claim 4, it is characterised in that：The maximum gauge t of the bleed blade with The scope of the ratio of the chord length b of the bleed blade is 0.05 to 0.3.

8. gas-turbine unit according to claim 4, it is characterised in that：The leading edge and/or tail of the bleed blade Edge is fillet.

9. gas-turbine unit according to claim 4, it is characterised in that：The interior casing includes being located at the bleed The upstream wall and the downstream wall positioned at the bleed ports downstream of mouth upstream；

The bleed blade is fixedly connected with the upstream wall and/or the bleed blade is fixed with the downstream wall and connected Connect.

10. gas-turbine unit according to claim 2, it is characterised in that：Interior casing includes being located at the bleed ports The upstream wall of upstream and the downstream wall positioned at the bleed ports downstream, the upstream wall and the downstream wall are integrated Structure.

11. gas-turbine unit according to claim 1, it is characterised in that：The entrance of the air flue and the circumferential direction The upper limit of angle be 15 degree or 20 degree or 25 degree, the entrance of the air flue and the lower limit of the circumferential angle are 50 degree or 60 Degree or 70 degree.

12. gas-turbine unit according to claim 1, it is characterised in that：The outlet of the air flue and the circumferential direction The upper limit of angle be 95 degree or 100 degree or 110 degree, the lower limit of the entrance of the air flue and the circumferential angle be 75 degree or 80 degree or 85 degree.

13. gas-turbine unit according to claim 1, it is characterised in that：The gas-turbine unit is aviation Engine, the downstream of the blade of the stator of the bleed ports setting compressor, the upstream of the blade of the rotor.

14. gas-turbine unit according to claim 1, it is characterised in that：The gas-turbine unit is combustion gas Turbine, the downstream of the blade of the rotor of the bleed ports setting compressor, the upstream of the blade of the stator.

15. gas-turbine unit according to claim 1, it is characterised in that：The compressor is axial-flow compressor.