CN210769380U - Turbofan engine and low-pressure compressor - Google Patents
Turbofan engine and low-pressure compressor Download PDFInfo
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- CN210769380U CN210769380U CN201921854763.7U CN201921854763U CN210769380U CN 210769380 U CN210769380 U CN 210769380U CN 201921854763 U CN201921854763 U CN 201921854763U CN 210769380 U CN210769380 U CN 210769380U
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Abstract
The utility model provides a low pressure compressor for turbofan engine, low pressure compressor include along the direction of admitting air set up in partial high rotor of leaf and partial high stator of leaf between booster stage export stage stator and the entailed extension board, and partial high rotor of leaf and partial high stator of leaf all have the blade root in low pressure compressor wheel hub side, and the high size of leaf of partial high rotor of leaf and partial high stator of leaf is a part of the high size of leaf of booster stage export stage stator respectively. The utility model also provides a turbofan engine including above-mentioned low pressure compressor. The low-pressure compressor can solve the problem that the root of the outlet stage of the booster stage is loaded heavily so that the aerodynamic stability is influenced or the root boosting capacity of the low-pressure compressor is insufficient.
Description
Technical Field
The utility model relates to a turbofan engine, in particular to low pressure compressor for turbofan engine.
Background
Modern fan boost stages are continually moving toward higher pressure ratios and higher stage loads. The supercharging stage can improve the pneumatic performance of a front low-pressure compressor and a rear high-pressure compressor on a turbofan engine, and the performance of the supercharging stage directly influences the efficiency, pressure ratio, stability margin and other pneumatic parameters of the engine.
For connection to the high-pressure compressor, the booster stage outlet stage is usually designed as a hold-down flow path and is then switched to the high-pressure compressor via a flow channel comprising a bypass strut. The design of the downward pressure flow path can lead to the increase of the load of the outlet stage of the booster stage, and the fluid tends to migrate towards the casing under the influence of centrifugal force, thereby being beneficial to the flow field at the tip of the outlet stage of the booster stage, but further intensifying the adverse pressure gradient of the root, leading to the easy occurrence of flow separation of the root and increasing the aerodynamic loss; in addition, according to the radial balance relationship, when the flow of the inlet of the compressor is reduced, the axial speed is reduced in a hub area and is serious near a tip area, so that the problem of insufficient power-applying capacity easily occurs when the root of the low-pressure compressor is in a near-instability state, the improvement of the efficiency and stability margin of the low-pressure compressor is limited by the factors, and the inlet of the high-pressure compressor is also faced with the problem of weak total pressure of the root, so that the improvement of the performance of the whole engine is influenced.
Therefore, an aerodynamic layout capable of increasing the total pressure at the outlet of the booster stage and achieving good flow of the low-pressure compressor is urgently needed.
SUMMERY OF THE UTILITY MODEL
The utility model discloses an aim at solve the problem that therefore the pressurization level export level root heavy load influences the aerodynamic stability.
Another object of the utility model is to solve the problem that the root pressure boost ability of low pressure compressor is not enough.
The utility model provides a low-pressure compressor which is used for a turbofan engine and sequentially comprises a booster stage outlet stage rotor, a booster stage outlet stage stator and an inner culvert support plate from upstream to downstream along the air inlet direction, the booster stage outlet stage rotor and the booster stage outlet stage stator each have a blade root on the low-pressure compressor hub side and a blade tip on the booster stage casing side, and has a blade height dimension extending from a blade root to a blade tip, the low-pressure compressor further comprises a part of blade height rotor and a part of blade height stator which are arranged between the booster stage outlet stage stator and the inner culvert supporting plate along the air inlet direction, the partial-vane-height rotor and the partial-vane-height stator each have a vane root on the hub side of the low-pressure compressor, the blade height dimensions of the partial-blade-height rotor and the partial-blade-height stator are respectively a part of the blade height dimensions of the booster stage outlet stage stator.
In one embodiment, the partial-height rotor and the partial-height stator have a height dimension that is between 15% and 35% of a height dimension of the booster stage outlet stage stator.
In one embodiment, the partial-vane high rotor and the partial-vane high stator have vane tips that are distal from the hub side of the low pressure compressor, and the vane tip profiles of the partial-vane high rotor and the partial-vane high stator are designed along a flow line.
In one embodiment, the leading edge line of the partial-height rotor is parallel to the trailing edge line of the booster stage outlet stage stator, the trailing edge line of the partial-height rotor being perpendicular to the low pressure compressor hub line or parallel to the leading edge line of the partial-height rotor.
In one embodiment, a leading edge line of the partial-blade-height stator is parallel to a trailing edge line of the partial-blade-height rotor, and the trailing edge line of the partial-blade-height stator is parallel to a leading edge line of the endoscopical support plate.
In one embodiment, the axial chord lengths of the partial-vane-height rotor and the partial-vane-height stator are the same.
In one embodiment, the axial distance between the partial-height rotor and the booster stage outlet stage stator, the axial distance between the partial-height rotor and the partial-height stator, and the axial distance between the partial-height stator and the inclusion plate are 15% to 25% of the axial chord length of the partial-height rotor.
In one embodiment, the blade consistency of the partial-blade-height rotor and the partial-blade-height stator is in a range of 0.9-1.5.
In one embodiment, the turning angle of the air flow of the rotor with the partial blade height and the stator with the partial blade height ranges from 10 degrees to 15 degrees.
The utility model also provides a turbofan engine, including foretell low pressure compressor.
In the low-pressure compressor of the turbofan engine, by the pneumatic layout of arranging the part of the blade-height rotor and the part of the blade-height stator between the outlet of the outlet stage of the supercharging stage and the culvert supporting plate, part of load can be shared by the part of the blade-height rotor and the part of the blade-height stator, so that the blade-shape bend angle of the outlet stage of the supercharging stage can be properly reduced when the blade shape of the root is designed, the load of the outlet stage of the supercharging stage, particularly the root, is reduced under the condition that the total pressure ratio of the low-pressure compressor is not changed, the working stability of the low-pressure compressor is improved, and the problem that the pneumatic stability is influenced by the negative load of the.
In addition, a part of blade height rotor and a part of blade height stator are arranged between the outlet of the boosting stage outlet stage and the inner culvert support plate, so that the flow field of the low-pressure compressor, particularly the root of the boosting stage outlet stage, can be improved, the stability margin is improved, and the problem of insufficient root boosting capacity of the low-pressure compressor can be solved.
In addition, the pneumatic layout of the low-pressure compressor does not change the consistency of the pressurization level, does not affect the middle part and the tip part of the pressurization level with better flow state, and effectively utilizes the space between the pressurization level and the culvert support plate. Moreover, the weight added by the rotor and stator of part of the blade height is limited.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
fig. 1 is a schematic view of the aerodynamic layout of a turbofan engine including a low pressure compressor of the present invention.
Fig. 2 is a partially enlarged view of the vicinity of a rotor and a stator of a partial blade height.
Fig. 3 is a schematic cross-sectional view taken along the flow line a-a in fig. 1.
FIG. 4 is a schematic illustration of a speed triangle of a boost stage outlet stage rotor.
FIG. 5 is a schematic view of the airflow direction of a booster stage outlet stage stator.
Fig. 6A and 6B show blade surface limit streamline views of a booster stage outlet stage stator at low load and at high load, respectively.
Detailed Description
The present invention will be further described with reference to the following detailed description and the accompanying drawings, wherein the following description sets forth more details for the purpose of providing a thorough understanding of the present invention, but it is obvious that the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar generalizations and deductions based on the practical application without departing from the spirit of the present invention, and therefore, the scope of the present invention should not be limited by the contents of the detailed description.
For example, a first feature described later in the specification may be formed over or on a second feature, and may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features may be formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated in the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
For convenience in description, spatial relational terms such as "below," "beneath," "below," "under," "over," "upper," and the like may be used herein to describe one element or feature's relationship to another element or feature as illustrated in the figures. It will be understood that these terms of spatial relationship are intended to encompass other orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" the other elements or features. Thus, the exemplary words "below" and "beneath" can encompass both an orientation of up and down. The device may have other orientations (rotated 90 degrees or at other orientations) and the spatial relationship descriptors used herein should be interpreted accordingly. Further, it will also be understood that when a layer is referred to as being "between" two layers, it can be the only layer between the two layers, or one or more intervening layers may also be present.
The terms "parallel," "perpendicular," "same," and the like, as used throughout, refer to similar terms and do not require the exact presence of "parallel," "perpendicular," "same," and the like. For example, "parallel" may indicate that the angle of intersection between two lines is within 10 degrees, "perpendicular" may indicate that the angle of intersection between two lines is within 10 degrees around 90 degrees, "identical" allows for two values to be within 10% of each other.
As used herein, the turning angle of the air flow is the angle between the inlet air flow angle and the outlet air flow angle, the blade bend angle is the angle between the metal inlet angle and the metal outlet angle of the blade, and the turning angle of the air flow is equal to the blade bend angle plus the angle of attack and minus the drop angle. Generally, under the condition that the air flows are not separated, the blade-shaped bent angle is increased, the air flow turning angle is increased, the blade-shaped bent angle is reduced, and the air flow turning angle is also reduced.
It should be noted that these and other figures are given by way of example only and are not drawn to scale, and should not be construed as limiting the scope of the invention as it is actually claimed. Further, the conversion methods in the different embodiments may be appropriately combined.
Fig. 1 shows schematically the aerodynamic layout of a turbofan engine 100 comprising a low pressure compressor 1 according to the invention. Also shown in FIG. 1 are fan rotor blades 101 and a bypass outlet 102 of turbofan engine 100. The turbofan engine 100 is fed from the left side in fig. 1 and discharged from the right side, showing the direction of feed C0 in the low pressure compressor 1, and is referred to as an upstream side near the feed side or left side in fig. 1 and a downstream side near the discharge side or right side in fig. 1. The axial direction X0 of the turbofan engine 100 or the low pressure compressor 1 is also shown. In the turbofan engine 100, the supercharging stage and the fan content portion are collectively called a "low-pressure compressor", and the supercharged and constant-flow-rate gas is introduced into the high-pressure compressor.
Referring to fig. 1, the low-pressure compressor 1 includes, in order from upstream to downstream in an intake direction C0, a booster stage outlet stage rotor 3, a booster stage outlet stage stator 4, and a bypass support plate 7. The boost stage outlet stage rotor 3 and boost stage outlet stage stator 4 may be collectively referred to as a "boost stage outlet stage".
The low-pressure compressor 1 also has a low-pressure compressor hub 9 and a pressure stage casing 10, wherein the low-pressure compressor hub 9 has a low-pressure compressor hub 91. In general, a low-pressure compressor 1 has a booster inlet guide vane 2 on the upstream side of a booster stage outlet stage rotor 3 and a low-pressure compressor outlet 8 on the downstream side of a bypass support plate 7.
The booster stage outlet stage rotor 3 and the booster stage outlet stage stator 4 each have a blade root on the low-pressure compressor hub 9 side (lower side in fig. 1) and a blade tip on the booster stage casing 10 side (upper side in fig. 1), and have a blade height dimension extending from the blade root to the blade tip. For example, as shown in FIG. 1, the booster stage outlet stage stator 4 has a root 44 (shown as a root profile, hereinafter also referred to as a root profile 44) on the low pressure compressor hub 9 side and a tip 42 (shown as a tip profile, hereinafter also referred to as a tip profile 42) on the booster stage casing 10 side. The height dimension H4 of the booster stage outlet stage stator 4 may be, for example, the length of the line connecting the midpoint of the root profile 44 and the midpoint of the tip profile 42 as shown in fig. 1, the length of the leading edge line 42 of the booster stage outlet stage stator 4, or the length of the trailing edge line 43 of the booster stage outlet stage stator 4, as long as the definitions of the different components are uniform.
The low-pressure compressor 1 further comprises a partial blade height rotor 5 and a partial blade height stator 6, wherein the partial blade height rotor 5 and the partial blade height stator 6 are arranged between the booster stage outlet stage stator 4 and the inner bypass support plate 7 along the air inlet direction C0. For example, the partial-height rotor 5 and the aforementioned booster stage outlet stage rotor 3 may be provided as rotor blades, which are mounted on a rotating shaft (not shown) to coaxially rotate in the same direction as the rotating shaft, and function as a diffuser. And part of the blade height stator 6 and the booster stage outlet stage stator 4 can be used as static blades and are arranged on a low-pressure compressor hub 9 to play roles of flow guiding and pressure expanding.
Fig. 2 shows a partial enlarged view of the vicinity of the rotor 5 and the stator 6 of the partial blade height. The partial-blade-height rotor 5 and the partial-blade-height stator 6 each have a blade root 54, 64 on the low-pressure compressor hub 9 side (both shown as blade root profiles, which may also be referred to below as blade root profiles 54, 64). The blade height dimensions H5, H6 of the partial-height rotor 5 and the partial-height stator 6 are respectively a portion of the blade height dimension H4 of the booster stage outlet stage stator 4, and in the figure, the blade height dimensions H5, H6 of the partial-height rotor 5 and the partial-height stator 6 are respectively the lengths of the connecting lines of the root profiles 54, 64 and the midpoints of the tip profiles 52, 62, in accordance with the definition of the blade height dimension H4 of the booster stage outlet stage stator 4 described above. Here, "a part of the blade height dimension H4" means less than 100% of the blade height dimension H4, that is, the blade height dimensions H5, H6 of the partial-blade-height rotor 5 and the partial-blade-height stator 6 are each less than the blade height dimension H4 of the booster stage outlet stage stator 4, and the blade height dimensions H5, H6 may be different from each other. Specifically, the height dimension of the partial-height rotor 5 and the partial-height stator 6 is 15% to 35% of the height dimension of the outlet-stage stator 4 of the booster stage, and as can be seen in fig. 6A and 6B, the height of the separated flow at low load is about 15% of the radial height of the blades, and the height of the separated flow at high load is about 35% of the radial height of the blades. Thus, the load of the root of the booster stage outlet stage rotor 3 and the booster stage outlet stage stator 4 within about 35% of the blade height range can be reduced, so that root separation is inhibited, and the stable working range of the low-pressure compressor is enlarged.
By designing a row of partial blade height rotors 5 and a row of partial blade height stators 6 behind a booster stage outlet stage stator 4, the air flow in the blade height range (for example, 35% blade height range) of the root part of the booster stage outlet stage can be boosted, the low-pressure air compressor 1 can flow well on the premise of ensuring that a fan booster stage compression system is not changed, and the boosting ratio of the root part of the low-pressure air compressor 1 can be effectively improved; or, under the condition of ensuring that the total pressure ratio of the low-pressure compressor is not changed, the diameter of the pressure stage can be properly reduced by the pneumatic layout, so that the weight of the low-pressure compressor 1 is reduced, and the weight caused by a part of the blade height rotor 5 and a part of the blade height stator 6 is offset or even greater.
Referring to fig. 2, the partial-vane-height rotor 5 and the partial-vane-height stator 6 have vane tips 52, 62 (shown as a root profile, which may also be referred to as a root profile 64 hereinafter) away from the hub side of the low-pressure compressor, the vane tip profiles 52, 62 of the partial-vane-height rotor 5 and the partial-vane-height stator 6 may be designed along the flow lines, or the vane tip profiles 52, 62 may be designed to be substantially streamlined to reduce the influence of the partial-vane-height rotor 5 and the partial-vane-height stator 6 on the flow field above the vane.
The leading edge line 51 of the partial-lobe rotor 5 may be approximately parallel to the trailing edge line 43 of the booster stage outlet stage stator 4, and the trailing edge line 53 of the partial-lobe rotor 5 may be approximately perpendicular to the low pressure compressor hub line 91 or may be approximately parallel to the leading edge line 51 of the partial-lobe rotor 5. The trailing edge line 53 of the partial-lobe rotor 5 may also be approximately perpendicular to the streamlines.
The leading edge line 61 of the partial-blade-height stator 6 may be approximately parallel to the trailing edge line 53 of the partial-blade-height rotor 5, and the trailing edge line 63 of the partial-blade-height stator 6 may be approximately parallel to the leading edge line 71 of the connotation plate 7.
Fig. 3 shows a schematic cross-sectional view along the flow line a-a in fig. 1, wherein the axial direction X0 and the direction of rotation or circumferential direction R0 of the turbofan engine 100 or low pressure compressor 1 are shown. The axial chord length Car of the partial-vane-height rotor 5 may be close to the axial chord length Cas of the partial-vane-height stator 6, for example, Car and Cas are the same. Referring to fig. 3, the axial distance C1 between the partial-vane-height rotor 5 and the booster stage outlet stage stator 4, the axial distance C2 between the partial-vane-height rotor 5 and the partial-vane-height stator 6, and the axial distance C3 between the partial-vane-height stator 6 and the inclusion plates may be 15% to 25% of the axial chord length Car of the partial-vane-height rotor 5. As shown in fig. 3, the axial distance C1 is the distance between the trailing edge line 43 of the booster stage outlet stage stator 4 and the leading edge line 51 of the partial-vane-height rotor 5 in the axial direction X0, the axial distance C2 is the distance between the trailing edge line 53 of the partial-vane-height rotor 5 and the leading edge line 61 of the partial-vane-height stator 6 in the axial direction X0, and the axial distance C3 is the distance between the trailing edge line 63 of the partial-vane-height stator 6 and the leading edge line 71 of the intensional plate 7 in the axial direction X0. The axial chord lengths Car, Cas or the axial distances C1, C2 and C3 or the spacings, consistencies mentioned below, etc. can be different on different cross sections taken along different streamlines of the blade height dimension, while the dimensional relationships involved are for the same cross section.
With continued reference to fig. 3, the partial-lobe rotor 5 and the partial-lobe stator 6 each have a circumferential spacing br, bs. For example, as shown in fig. 3, the circumferential pitch br may be a pitch between two partial blade height rotors 5 adjacent in the circumferential direction R0, more specifically, may be a distance between leading edge lines 51 of the two partial blade height rotors 5 in the circumferential direction R0; the circumferential pitch bs may be a pitch between two partial vane height stators 6 adjacent in the circumferential direction R0, and more specifically, may be a distance between leading edge lines 61 of the two partial vane height stators 6 in the circumferential direction R0. The partial-vane-height rotor 5 and the partial-vane-height stator 6 also each have an actual chord length Cr, Cs. As shown in fig. 3, the actual chord length Cr is the length of the straight line connecting the leading edge line 51 and the trailing edge line 53 of the partial blade height rotor 5, and the actual chord length Cs is the length of the straight line connecting the leading edge line 61 and the trailing edge line 63 of the partial blade height stator 6. The partial-height rotor 5 and the partial-height stator 6 have blade consistencies Cr/br, Cs/bs, respectively. The blade numbers of the partial-blade-height rotor 5 and the partial-blade-height stator 6 are respectively determined by the blade consistencies Cr/br and Cs/bs thereof, the blade consistencies Cr/br and Cs/bs can be determined by the load rationality, and the load rationality can be referred to according to standards or manuals. The consistency range of the blades of the partial blade height rotor 5 and the partial blade height stator 6 can be 0.9-1.5, namely, Cr/br and Cs/bs are 0.9-1.5, so as to adapt to the rationality of the load.
The turning angle ranges of the air flows of the rotor 5 with partial blade height and the stator 6 with partial blade height can be both 10 degrees to 15 degrees. The roots of the rotor 3 and the stator 4 at the outlet stage of the booster stage can respectively reduce the turning angle of the airflow by 5-15 degrees. The turning angle of the air flow is the change in the flow direction of the air flow as it flows through the vane passage. In fig. 3, taking the booster stage outlet stage rotor 3 as an example, the angle between the blade inlet airflow direction of the booster stage outlet stage rotor 3 and the axial direction X0 is θ 1, the angle between the outlet airflow direction of the booster stage outlet stage rotor 3 and the axial direction X0 is θ 2, and the difference Δ θ 1 between θ 1 and θ 2, where θ 1- θ 2 represents the relative airflow turning angle of the booster stage outlet stage rotor 3. Fig. 3 also shows the location of the various sections generally schematically in dashed lines, B1 representing the inlet section of the booster stage outlet stage rotor 3, B2 representing the outlet section of the booster stage outlet stage stator 4, B3 representing the inlet section of the part-bladed rotor 3, B4 representing the outlet section of the part-bladed rotor 3, and B5 representing the outlet section of the part-bladed stator 4.
Compared with the existing design scheme, the turning angles of the inlet and outlet air flows of the booster stage outlet stage rotor 3 and the turning angles of the inlet and outlet air flows of the booster stage outlet stage stator 4 are both reduced, the load is both reduced, and partial load is borne by partial blade height rotors and partial blade height stators. Since the flow is good at this time, the layout also has less influence on the flow.
Fig. 4 shows the speed triangle of the booster stage outlet stage rotor 3. In fig. 4, W1 represents the inlet airflow relative velocity of boost stage outlet stage rotor 3, W2 represents the outlet airflow relative velocity of boost stage outlet stage rotor 3, W2 'represents the outlet airflow relative velocity of boost stage outlet stage rotor 3 after the lobe angle is decreased, V1 represents the inlet airflow absolute velocity of boost stage outlet stage rotor 3, V2 represents the outlet airflow absolute velocity of boost stage outlet stage rotor 3, V2' represents the outlet airflow absolute velocity of boost stage outlet stage rotor 3 after the lobe angle is decreased, and U represents the rotor rim velocity. Referring to fig. 4, after the blade-shaped bend angle is reduced, the turning angle of the inlet/outlet airflow of the booster stage outlet stage rotor 3 is changed from Δ θ 1,2 to Δ θ '1, 2, and the angle between the outlet airflow direction of the booster stage outlet stage rotor 3 and the axial direction is changed from θ 2 to θ' 2. Fig. 5 shows the air flow direction of the booster stage outlet stage stator 4, wherein the booster stage outlet stage stator 4 has a blade bowl 41 and a blade back 42. As shown in fig. 5, when the angle between the outlet airflow direction of the booster stage outlet stage rotor 3 and the axial direction is changed from θ 2 to θ '2, the angle between the inlet airflow direction of the booster stage outlet stage stator 4 and the axial direction is changed from θ 2 to θ' 2, so that the turning angle of the airflow is reduced, and the load of the booster stage outlet stage stator 4 is also reduced.
Under the conditions that the low-pressure compressor has heavy load and poor flowing state, the flowing state of the outlet stage of the pressurizing stage is the worst in the whole pressurizing stage due to the fact that the runner is pressed down, and the outlet stage of the pressurizing stage is easy to enter the unstable state firstly. At the moment, the turning angle of the air flow at the inlet and the outlet of the booster stage outlet stage rotor 3 is reduced from delta theta 12 to delta theta' 1 and 2, the load of the root is reduced, and the root separation is favorably inhibited.
As shown in fig. 4 and 5, the inlet airflow angle of the stator at the outlet of the booster stage is reduced from θ 2 to θ' 2, which is equivalent to the inlet airflow angle moving toward the blade back 42, so that the inlet flow field of the blade working in a low flow state is improved, and the root load is reduced because the turning angle of the airflow is also reduced, which is beneficial to inhibiting the root separation. Partial blade height stators bear partial load of the outlet stage of the booster stage, so that the root flow of the outlet stage of the booster stage is improved, and the effect of stability expansion can be achieved while the total pressure ratio of the low-pressure compressor is not changed.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.
Claims (10)
1. A low-pressure compressor for a turbofan engine includes, in order from upstream to downstream in an intake direction, a booster stage outlet stage rotor, a booster stage outlet stage stator, and an inclusion support plate, the booster stage outlet stage rotor and the booster stage outlet stage stator each having a blade root on a hub side of the low-pressure compressor and a blade tip on a casing side of the booster stage, and having a blade height dimension extending from the blade root to the blade tip,
the low-pressure compressor is characterized by further comprising a partial blade height rotor and a partial blade height stator which are arranged between the booster stage outlet stage stator and the containing support plate along the air inlet direction, wherein the partial blade height rotor and the partial blade height stator are both provided with blade roots on the hub side of the low-pressure compressor, and the blade height sizes of the partial blade height rotor and the partial blade height stator are respectively a part of the blade height size of the booster stage outlet stage stator.
2. The low pressure compressor as claimed in claim 1 wherein the partial-lobe rotor and the partial-lobe stator have a lobe height dimension that is between 15% and 35% of a lobe height dimension of the booster stage outlet stage stator.
3. The low-pressure compressor as claimed in claim 1, characterized in that the partial-vane-height rotor and the partial-vane-height stator have vane tips which are remote from the hub side of the low-pressure compressor, the vane tip profiles of the partial-vane-height rotor and the partial-vane-height stator being designed along the flow line.
4. The low pressure compressor as claimed in claim 1, wherein the leading edge line of the partial-vane-height rotor is parallel to the trailing edge line of the booster stage outlet stage stator, the trailing edge line of the partial-vane-height rotor being perpendicular to the low pressure compressor hub line or parallel to the leading edge line of the partial-vane-height rotor.
5. The low pressure compressor as claimed in claim 1, wherein a leading edge line of the partial-vane-height stator is parallel to a trailing edge line of the partial-vane-height rotor, and the trailing edge line of the partial-vane-height stator is parallel to a leading edge line of the inclusion plate.
6. The low pressure compressor as claimed in claim 1, wherein axial chord lengths of the partial-vane-height rotor and the partial-vane-height stator are the same.
7. The low pressure compressor as claimed in claim 1 wherein the axial distance between the partial-height rotor and the discharge stage stator of the booster stage, the axial distance between the partial-height rotor and the partial-height stator, and the axial distance between the partial-height stator and the inclusion plate are 15% to 25% of the axial chord length of the partial-height rotor.
8. The low pressure compressor as claimed in claim 1, wherein the blade consistency of the partial-height rotor and the partial-height stator is in the range of 0.9 to 1.5.
9. The low pressure compressor as claimed in claim 1, wherein the turning angle of the air flow of the rotor with partial blade height and the stator with partial blade height is in the range of 10 ° to 15 °.
10. Turbofan engine characterized by comprising a low-pressure compressor according to any of claims 1 to 9.
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| CN201921854763.7U CN210769380U (en) | 2019-10-31 | 2019-10-31 | Turbofan engine and low-pressure compressor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113062777A (en) * | 2021-06-03 | 2021-07-02 | 中国航发上海商用航空发动机制造有限责任公司 | Performance debugging method of booster stage and turbofan engine |
| CN113090412A (en) * | 2021-06-08 | 2021-07-09 | 中国航发上海商用航空发动机制造有限责任公司 | Supercharging stage device and turbofan engine |
| CN113738532A (en) * | 2021-11-04 | 2021-12-03 | 中国航发沈阳发动机研究所 | Aero-engine with overlapped ducts |
| CN113738531A (en) * | 2021-11-03 | 2021-12-03 | 中国航发沈阳发动机研究所 | Indirect cooling type high-total-pressure-ratio middle duct turbofan engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113062777A (en) * | 2021-06-03 | 2021-07-02 | 中国航发上海商用航空发动机制造有限责任公司 | Performance debugging method of booster stage and turbofan engine |
| CN113090412A (en) * | 2021-06-08 | 2021-07-09 | 中国航发上海商用航空发动机制造有限责任公司 | Supercharging stage device and turbofan engine |
| CN113738531A (en) * | 2021-11-03 | 2021-12-03 | 中国航发沈阳发动机研究所 | Indirect cooling type high-total-pressure-ratio middle duct turbofan engine |
| CN113738531B (en) * | 2021-11-03 | 2022-02-18 | 中国航发沈阳发动机研究所 | Indirect cooling type high-total-pressure-ratio middle duct turbofan engine |
| CN113738532A (en) * | 2021-11-04 | 2021-12-03 | 中国航发沈阳发动机研究所 | Aero-engine with overlapped ducts |
| CN113738532B (en) * | 2021-11-04 | 2022-02-18 | 中国航发沈阳发动机研究所 | Aero-engine with overlapped ducts |
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