Compressor shaft for an aircraft turbine engine
By using a segmented compressor shaft design and connecting the shaft collar and the main body with a fork-shaped part, the problem of insufficient compressor shaft stiffness was solved, the stiffness was improved and the impact of increased mass on fuel consumption was reduced, thus optimizing the performance of the turbine engine.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2024-10-08
- Publication Date
- 2026-06-05
AI Technical Summary
In the existing technology, the compressor shaft stiffness of aircraft turbine engines is insufficient, which causes the bearings to bear excessive stress, and increasing the shaft mass will increase fuel consumption.
The compressor shaft adopts a segmented design, with the shaft collar connected to the main body via a fork-shaped part. The thickness and shape of the upstream and downstream arms are optimized to meet rigidity requirements and limit the increase in mass.
The radial and rotational stiffness of the compressor shaft was improved, the impact of increased mass on fuel consumption was reduced, and the performance of the turbine engine was optimized.
Smart Images
Figure CN122161987A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a compressor shaft for an aircraft turbine engine, and to an aircraft turbine engine including such a compressor shaft. Background Technology
[0002] The "open fan" turbine engine includes a non-ducted movable fan and a non-ducted fixed flow straightener, the non-ducted movable fan being driven to rotate by a power turbine (or low-pressure turbine), and the non-ducted fixed flow straightener being configured to straighten at least a portion of the airflow generated by the non-ducted fan.
[0003] This high-bypass turbofan engine has the advantage of excellent efficiency, especially in reducing fuel consumption and carbon dioxide emissions.
[0004] Typically, a power turbine is associated with a gas generator, which includes at least one compressor, a combustion chamber, and at least one expansion turbine (or high-pressure turbine). More specifically, the power turbine is driven to rotate by gas exiting the expansion turbine.
[0005] To optimize the performance of "open fan" turbine engines, it is known to install a movable ducted fan and a low-pressure compressor (often called a "booster") in the intake of the gas generator. This ducted fan is often referred to as an "intermediate fan".
[0006] This type of ducted fan can be driven to rotate together with the rotor of a low-pressure compressor via a compressor shaft, which is driven to rotate by a power turbine.
[0007] To achieve this, engine manufacturers envision clamping the rotors of the ducted fan and the low-pressure compressor together onto a collar on the compressor shaft. This shaft with the collar is traditionally a single piece, manufactured, for example, by turning.
[0008] However, the initial results obtained through calculations indicate that, based on the first assumption of the solution, the compressor shaft has too low a stiffness compared to the predefined stiffness in the technical specifications, which take into account the vibration behavior of the turbine engine. If the stiffness is too low, the bearings used to guide the compressor shaft will be subjected to excessive stress.
[0009] One solution to further strengthen the compressor shaft (especially the compressor shaft collar) could be to increase its thickness. This solution provides a slight increase in stiffness, but significantly increases the mass of the compressor shaft, thereby increasing the fuel consumption of the turbine engine, which is undesirable.
[0010] Therefore, the object of this invention is to provide a solution that increases the stiffness of the compressor shaft to meet the requirements of the specification, while minimizing the increase in the mass of the compressor shaft.
[0011] Existing technologies also include documents US2010 / 124495A1, US2021 / 310417A1, US2023 / 160395A1, WO2022 / 153000A1 and US5211541A. Summary of the Invention
[0012] Therefore, the present invention provides a compressor shaft for an aircraft turbine engine, the shaft being integral and annular about a longitudinal axis X, the shaft comprising a longitudinally extending body and a collar extending substantially radially relative to the axis X, the collar having an outer end of a bearing flange and an inner end connected to the body, the flange being configured to be fixed to the rotor of a ducted fan and a low-pressure compressor. The feature is that the body is divided into an upstream portion and a downstream portion that are longitudinally spaced apart from each other. The inner end of the collar is connected to the upstream portion and the downstream portion of the body via a forked portion. The forked portion includes an upstream arm and a downstream arm. The upstream arm connects the inner end of the collar to the downstream end of the upstream portion of the body, and the downstream arm connects the inner end of the collar to the upstream end of the downstream portion of the body, such that the upstream arm and the downstream arm form an opening recess on the inner side. The upstream arm includes an inner surface that is axially and directly opposite to the inner surface of the downstream arm.
[0013] Using a forked part to connect the collar to the body not only meets the technical specifications in terms of stiffness (radial stiffness and rotational stiffness), but also limits the impact on mass.
[0014] The shaft according to the invention may include one or more features that are used independently or in combination with each other: - The thickness of the upstream arm is greater than the thickness of the downstream arm; - The thickness of the upstream arm gradually increases from the downstream end of the upstream portion of the body to the inner end of the collar; -The flange is axially located upstream of the fork-shaped portion; - The collar extends in the extension of the downstream arm; - The inner and outer surfaces of the downstream arm each expand from downstream to upstream, and expand continuously from the upstream end of the downstream portion of the body to the inner end of the collar; - The collar expands from downstream to upstream, and from the inner end of the collar to the outer end of the collar; - The inner and outer surfaces of the upstream arm each expand from upstream to downstream, and expand continuously from the downstream end of the upstream portion of the body to the inner end of the collar; - The inner and outer surfaces of the upper arm form an acute angle A with each other, which is defined in a half-section. The cross-sectional plane of the half-section is longitudinal and passes through the axis X. Preferably, the acute angle A is between 5° and 15°. - The inner surfaces of the upstream arm and the downstream arm are connected by fillets, preferably with a radius R between 10 mm and 30 mm. - The maximum radial dimension D of the concave portion is greater than the corresponding maximum radial dimensions D1 and D2 of the upstream and downstream portions; - The recess includes a bottom that is located radially outward relative to the inner ends of each of the inner ends of the upstream and downstream arms; -The upstream and downstream parts of the main body are each cylindrical; - The upstream arm and the downstream arm form an interior angle of less than 100° with each other, which is defined in the half-section, the cross-sectional plane of which is longitudinal and passes through the axis X; - Both the upstream and downstream arms are tapered; - The downstream end of the upstream portion of the main body and the upstream end of the downstream portion of the main body are separated from each other and are axially separated from each other by a recess.
[0015] The present invention also relates to a turbine engine for an aircraft, the turbine engine comprising: - A gas generator, which is supplied with gas through an inlet; - A power turbine that operates independently of the gas generator; - A low-pressure compressor, which includes a rotor that is driven to rotate by a power turbine; - Non-ducted fan, which is capable of rotational motion and is driven to rotate by a power turbine; - A non-ducted flow straightener that is fixed in terms of rotation; - Ducted fan, which is located in the air intake and is capable of rotational motion and is driven to rotate by a power turbine; The rotors of the ducted fan and the low-pressure compressor are driven to rotate by a power turbine via the compressor shaft as described above.
[0016] The turbine engine according to the present invention may include one or more features that are used independently or in combination with each other: - The ducted fan includes a flange, the rotor of the low-pressure compressor includes a drum, the drum includes a flange, and the flange of the ducted fan, the flange of the compressor shaft and the flange of the drum are fixed to each other by a ring-shaped bolt. - Non-ducted fans are driven to rotate by a power turbine via a reducer; - The upstream end of the upstream section of the compressor shaft is rotatably connected to the input element of the reducer, and the non-ducted fan is rotatably connected to the output element of the reducer; - The non-ducted fan includes an annular row of variable pitch blades, and the non-ducted flow straightener includes an annular row of variable pitch outlet guide blades. Attached Figure Description
[0017] The invention will be better understood in the following description by way of non-limiting example and with reference to the accompanying drawings, and other details, features and advantages of the invention will become clearer, as illustrated in the drawings: [ Figure 1 ] Figure 1 This is a schematic longitudinal section half-view of an aircraft turbine engine according to the present invention; [ Figure 2 ] Figure 2 yes Figure 1 A detailed view showing the connection between the compressor shaft, the rotor of the low-pressure compressor, and the ducted fan; [ Figure 3 ] Figure 3 yes Figure 1 and Figure 2 A perspective view of the compressor shaft shown; [ Figure 4 ] Figure 4 This is a detailed view of the compressor shaft at the fork-shaped section. Detailed Implementation
[0018] Figure 1 A turbine engine 1 for use in a flight vehicle 2 (such as an airplane) is shown.
[0019] Turbine engine 1 includes: - Gas generator 3, which is supplied with gas by the air inlet; - Power turbine 5 (or low-pressure turbine), which is independent of gas generator 3; - Low-pressure compressor 6 (commonly referred to as a booster), which includes a rotor 7 driven to rotate by a power turbine 5; - Non-ducted fan 8, which is capable of rotational motion and is driven to rotate by power turbine 5; - Non-ducted flow straightener 9, which is fixed in terms of rotation; - Ducted fan 10, which is arranged in the air intake 4, is capable of rotational movement and is driven to rotate by a power turbine 5.
[0020] The rotor 7 of the ducted fan 10 and the low-pressure compressor 6 are jointly driven to rotate by the power turbine 5 via the compressor shaft 11 according to the invention.
[0021] The term “non-ducted” associated with fan 8 means that the blades 21 of fan 8 are not surrounded by a fairing at their free ends.
[0022] Furthermore, the term "non-ducted" associated with the flow straightener 9 refers to the fact that the outlet guide vane 27 of the flow straightener 9 is not surrounded by a fairing at its free end.
[0023] Furthermore, the term "ducted" associated with fan 10 refers to the fact that the blades 32 of fan 10 are enclosed at their free ends by a fairing (in this case, a nacelle 28).
[0024] Finally, the term “independent” associated with the power turbine 5 means that the power turbine 5 is not rotatably connected to the gas generator 3.
[0025] The turbine engine 1 is defined along a longitudinal axis X, which in particular corresponds to the rotation axis of the rotor 7 of the non-ducted fan 8, the ducted fan 10, the compressors 6 and 12, and the turbines 5 and 14.
[0026] according to Figure 1 In the illustrated embodiment, the low-pressure compressor 6, gas generator 3, and power turbine 5 are arranged downstream of the non-ducted fan 8 and the ducted fan 10. Additionally, the low-pressure compressor 6 is located upstream of the gas generator 3, and the power turbine 5 is located downstream of the gas generator 3. The gas generator 3 is supplied with air via an inlet 4 that opens between the non-ducted fan 8 and the flow straightener 9. Typically, the gas generator 3 includes at least one high-pressure compressor 12, a combustion chamber 13, and at least one expansion turbine 14 (or high-pressure turbine). The rotors of the high-pressure compressor 12 and the expansion turbine 14 are rotatably connected via one or more drive shafts 15.
[0027] The rotor 7 and ducted fan 10 of the low-pressure compressor 6 are driven to rotate by the power turbine 5 via the compressor shaft 11 and the turbine shaft 16.
[0028] More specifically, such as Figure 1 As shown, the low-pressure compressor 6 includes two axial compression stages. The low-pressure compressor 6 includes a rotor 7, which includes a drum 17, to which two annular impeller blades 18 are mounted. The drum 17 includes a flange 19 fixed to the compressor shaft 11.
[0029] Here, the high-pressure compressor 12 includes five axial compression stages.
[0030] Combustion chamber 13 is supplied with compressed air via high-pressure compressor 12 and fuel via multiple injectors. The air / fuel mixture is combusted by multiple ignition devices. Exhaust gas from combustion chamber 13 expands in expansion turbine 14 and then in power turbine 5.
[0031] The expansion turbine 14 includes two axial expansion stages.
[0032] The power turbine 5 comprises four axial expansion stages. The power turbine 5 is driven to rotate by the exhaust gas exiting the expansion turbine 14, and the exhaust gas is then discharged through the nozzle 20.
[0033] Figure 1 The embodiments shown are not limiting. For example, compressors 6 and 12 and turbines 5 and 14 may include different numbers of stages. Generally, a compressor may include one or more axial and / or centrifugal compression stages. A turbine may include one or more axial and / or radial expansion stages.
[0034] like Figure 1 As shown, the non-ducted fan 8 is capable of rotational motion about axis X. The non-ducted fan 8 includes an annular row of variable-pitch blades 21, each blade 21 rotating about a rotation axis Y1 substantially perpendicular to axis X. The non-ducted fan 8 includes an adjustment system 22 for adjusting the pitch of the blades 21, which can be shared by all blades 21 or dedicated to each blade 21.
[0035] According to one example, the regulating system 22 includes an actuator common to all blades 21 and a mechanism dedicated to each blade 21, which enables the conversion of movement initiated by the actuator into rotational motion of the corresponding blade 21.
[0036] The non-ducted fan 8 is driven to rotate by the power turbine 5 via the reducer 23. Compared to the rotational speed of the power turbine, the reducer 23 reduces the rotational speed of the non-ducted fan 8 while increasing its torque. More specifically, the compressor shaft 11 is rotatably connected to the input element 24 of the reducer 23, and the non-ducted fan 8 is rotatably connected to the output element 25 of the reducer 23.
[0037] Advantageously, the reducer 23 is a gear reducer, preferably a rotary gear reducer. The advantage of a rotary reducer is that it has a high reduction ratio and is compact.
[0038] A rotary reducer includes at least one reduction stage, which comprises a sun gear (or planetary gear), a ring gear, planetary gears, and a planet carrier. Rotary reducers can be constructed in various ways.
[0039] In the first configuration, the sun gear is the input element 24 of the reducer 23, the ring gear is the output element 25 of the reducer 23, and the planet carrier is either fixed or stationary. In other words, the sun gear is rotatably connected to the compressor shaft 11, and the ring gear is rotatably connected to the non-ducted fan 8.
[0040] In the second configuration, the sun gear is the input element 24 of the reducer 23, the ring gear is fixed or stationary, and the planet carrier is the output element 25 of the reducer 23. In other words, the sun gear is rotatably connected to the compressor shaft 11, and the planet carrier is rotatably connected to the non-ducted fan 8.
[0041] The two configurations mentioned above are not exhaustive; other configurations are also possible, depending on the required reduction ratio.
[0042] Similarly, the reducer 23 with gear train may include one or more reduction stages.
[0043] The non-ducted fan 8 defines an enclosure 26 on the inside, in which a reducer 23 with a gear train is housed and lubricated.
[0044] When turbine engine 1 is in "thruster" mode, non-ducted fan 8 generates an airflow F that flows from upstream to downstream around the outer fairing of the molten body of turbine engine 1 to generate the main thrust that propels aircraft 2. Turbine engine 1 can also operate in "reverse" mode to brake aircraft 2 during landing.
[0045] As is customary in this application, when the turbine engine 1 is in "propeller" mode, the terms "upstream" and "downstream" are defined relative to the direction of airflow F.
[0046] like Figure 1 As shown, the non-ducted flow straightener 9 is fixed in rotation about axis X and is configured to straighten at least a portion of the airflow F generated by the non-ducted fan 8. The flow straightener 9 is located directly downstream of the non-ducted fan 8. The flow straightener 9 includes an annular outlet guide vane 27 (or stator vane or OGV vane) arranged in a regular pattern around the nacelle 28.
[0047] The outlet guide vane 27 has a variable pitch, and each outlet guide vane 27 rotates about a rotation axis Y2 that is substantially perpendicular to the axis X.
[0048] The flow straightener 9 includes a regulating system 29 for adjusting the pitch of the exit guide vanes 27, which can be shared by all exit guide vanes 27 or dedicated to each exit guide vane 27. One or more regulating systems 29 are located in an internal compartment 30 of the nacelle 28.
[0049] According to one example of an embodiment, the regulating system 29 includes an actuator common to all outlet guide vanes 27 and a mechanism dedicated to each outlet guide vane 27, which enables the conversion of movement initiated by the actuator into rotational motion of the corresponding outlet guide vane 27.
[0050] like Figure 1 As shown, the ducted fan 10 is located in the air intake 4 and is surrounded by the nacelle 28. The ducted fan 10 is commonly referred to as the "intermediate fan".
[0051] The ducted fan 10 is capable of rotating about axis X. The ducted fan 10 includes a disk 31 that carries an annular row of fixed-pitch blades 32. The blades 32 can be mounted on the disk 31, or they can be integrally formed with the disk 31 to form an integral blade disk.
[0052] The ducted fan 10 is driven to rotate by the power turbine 5 via the compressor shaft 11. More specifically, the disc 31 includes a flange 33 fixed to the compressor shaft 11.
[0053] The airflow generated by the ducted fan 10 is divided into a main airflow f1 and a secondary airflow f2 by the splitter nose 34 of the fixed structure 35 of the turbine engine 1. The main airflow f1 enters the main duct 36, which is configured to supply the gas generator 3, while the secondary airflow f2 flows around the low-pressure compressor 6 and the gas generator 3 in the secondary duct 37. The secondary airflow f2 contributes less to the thrust provided by the turbine engine 1.
[0054] In the remainder of the instruction manual, particular attention will be paid to the compressor shaft 11, which will be referred to as "shaft" 11 below.
[0055] In the same manner as the turbine engine 1, the compressor shaft 11 is defined along the longitudinal axis X.
[0056] Shaft 11 is integral and is annular (or rotatable) about a longitudinal axis X. Shaft 11 includes a longitudinally extending body 38 and a collar 39 that extends substantially radially relative to the axis X. The collar 39 has an outer end 40 that carries a flange 41 and an inner end 42 that connects to the body 38. The flange 41 is fixed to the rotor 7 of the ducted fan 10 and the low-pressure compressor 6.
[0057] According to the invention, the body 38 of the shaft 11 is divided into an upstream portion 44 and a downstream portion 45 that are longitudinally spaced apart from each other. The inner end portion 42 of the collar 39 is connected to the upstream portion 44 and the downstream portion 45 of the body 38 via a fork 46. The fork 46 includes an upstream arm 47 and a downstream arm 49, the upstream arm 47 connecting the inner end portion 42 of the collar 39 to the downstream end portion 48 of the upstream portion 44 of the body 38, and the downstream arm 49 connecting the inner end portion 42 of the collar 39 to the upstream end portion 50 of the downstream portion 45 of the body 38, such that the upstream arm 47 and the downstream arm 49 form a recess 51 on their inner sides that opens toward the axis X. The upstream arm 47 includes an inner surface 52 that is axially and directly opposite (or facing) the inner surface 54 of the downstream arm 49.
[0058] Using a forked part to connect the collar to the body not only meets the technical specifications in terms of stiffness (radial stiffness and rotational stiffness), but also limits the impact on mass.
[0059] Advantageously, the thickness E1 of the upstream arm 47 is greater than the thickness E2 of the downstream arm 49. In fact, regarding shaft stiffness, the engine manufacturer has already pointed out that the contribution of the upstream arm 47 is greater than that of the downstream arm 49.
[0060] Advantageously, the thickness E1 of the upstream arm 47 gradually increases from the downstream end 48 of the upstream portion 44 of the body 38 to the inner end 42 of the collar 39. This type of dimension is beneficial for increasing the stiffness of the shaft.
[0061] The flange 41 carried by the collar 39 can be axially located upstream of the fork 46, such that the collar is radially inclined away from the axis X from downstream to upstream.
[0062] The collar 39 can be extended as an extension of the downstream arm 49.
[0063] Advantageously, the upstream arm 47 and the downstream arm 49 are each truncated conical.
[0064] Advantageously, the downstream arm 49 extends from downstream to upstream and extends continuously (or uninterruptedly) from the upstream end 50 of the downstream portion 45 of the body 38 to the inner end 42 of the collar 39.
[0065] Advantageously, the inner and outer surfaces 54 of the downstream arm 49 each expand from downstream to upstream, and continuously expand from the upstream end 50 of the downstream portion 45 of the body 38 to the inner end 42 of the collar 39. In other words, the radial dimension of each of the inner and outer surfaces 54 of the downstream arm 49 increases from downstream to upstream, and continuously increases from the upstream end 50 of the downstream portion 45 of the body 38 to the inner end 42 of the collar 39.
[0066] The collar 39 can expand from downstream to upstream, and from its inner end 42 to its outer end 40.
[0067] Advantageously, the upstream arm 47 extends from upstream to downstream and extends continuously from the downstream end 48 of the upstream portion 44 of the body 38 to the inner end 42 of the collar 39.
[0068] Advantageously, the inner surface 52 and outer surface 53 of the upstream arm 47 each expand from upstream to downstream, and continuously expand from the downstream end 48 of the upstream portion 44 of the body 38 to the inner end 42 of the collar 39. In other words, the radial dimension of each of the inner surface 52 and outer surface 53 of the upstream arm 47 increases from upstream to downstream, and continuously increases from the downstream end 48 of the upstream portion 44 of the body 38 to the inner end 42 of the collar 39.
[0069] Advantageously, such as Figure 4 As shown, the inner surface 52 and outer surface 53 of the upstream arm 47 form an acute angle A between the inner and outer surfaces. The acute angle A is defined in the half of the cross-section where the cross-sectional plane is longitudinal and passes through the axis X. Preferably, the acute angle A is between 5° and 15°. This type of dimension is beneficial for increasing the stiffness of the shaft.
[0070] Advantageously, the inner surface 52 of the upstream arm 47 and the inner surface 54 of the downstream arm 49 are connected by a fillet 55, preferably with a radius R between 10 mm and 30 mm. This type of dimension increases the rigidity of the shaft and makes painting possible.
[0071] Advantageously, the maximum radial dimension D of the recess 51 is greater than the corresponding maximum radial dimensions D1 and D2 of the upstream portion 44 and the downstream portion 45. This dimension optimizes the shaft's stiffness to mass ratio.
[0072] Dimensions D1 and D2 can represent the order of magnitude of the radius associated with the inner bearing radius, which is designed to mate with an inner bearing ring that supports the rotation of shaft 11 relative to the environment in the turbine engine.
[0073] Advantageously, the recess 51 includes a bottom 55 that is located radially outward relative to the inner ends of each of the upstream arm 47 and the downstream arm 49.
[0074] The upstream portion 44 and the downstream portion 45 of the main body 38 can be cylindrical. Advantageously, the upstream arm 47 and the downstream arm 49 form an interior angle of less than 100° with each other, which is defined in the half of the cross-section where the cross-sectional plane is longitudinal and passes through the axis X.
[0075] Advantageously, the downstream end 48 of the upstream portion 44 of the body 38 and the upstream end 50 of the downstream portion 45 of the body 38 are separated (or separated) from each other and are axially separated from each other by the recess 51.
[0076] like Figure 1 and Figure 2 As shown, the flange 33 of the ducted fan 10, the flange 41 of the shaft 11, and the flange 19 of the drum 17 are secured to each other by a ring of bolts 56 around the axis X. Each bolt 56 includes a screw 57 and a nut 65, the shank of which passes through a through hole 58 formed in the flange 41 of the shaft 11, a through hole 59 formed in the flange 19 of the drum 17, and a through hole 60 formed in the flange 33 of the ducted fan 10. The flange 19 of the drum 17 is axially located between the flange 33 of the ducted fan 10 and the flange 41 of the shaft 11.
[0077] The flange 19 of the drum 17 includes an outer edge 61 projecting from the upstream surface of the flange 19, which facilitates the positioning of the flange 33 of the ducted fan 10. In addition, the flange 19 of the drum 17 includes an inner edge 62 projecting from the downstream surface of the flange 19, which facilitates the positioning of the flange 41 of the shaft 11.
[0078] The three bolt flanges 19, 33, and 41 are located upstream of the fork-shaped portion 46 of the shaft 11.
[0079] As shown in the figure, the collar 39 expands from downstream to upstream, from its inner end 42 to its outer end 40. The collar 39 extends as an extension of the downstream arm 49.
[0080] like Figure 2 and Figure 4 As shown, the upstream arm 47 and the downstream arm 49 of the fork-shaped portion 46 are axially and directly opposite each other. More specifically, the inner surface 52 of the upstream arm 47 and the inner surface 54 of the downstream arm 49 are axially and directly opposite each other.
[0081] like Figure 2 and Figure 4 As shown, the upstream arm 47 and downstream arm 49 of the fork-shaped portion 46 are asymmetrical with respect to the intermediate transverse plane of the fork-shaped portion 46. The upstream arm 47 and downstream arm 49 form an interior angle of approximately 90° between the upstream arm and downstream arm, which is defined in the half-section where the cross-sectional plane is longitudinal and passes through the axis X. The thickness E1 of the upstream arm 47 is greater than the thickness E2 of the downstream arm 49. The thickness E1 of the upstream arm 47 at its base is 14.5 mm, and the constant thickness E2 of the downstream arm 49 is 12 mm.
[0082] More specifically, such as Figure 4As shown, the upstream arm 47 is a truncated cone shape. The upstream arm 47 expands from upstream to downstream, and continuously expands from the downstream end 48 of the upstream portion 44 of the body 38 to the inner end 42 of the collar 39. More specifically, the inner surface 52 and outer surface 53 of the upstream arm 47 each expand from upstream to downstream, and continuously expand from the downstream end 48 of the upstream portion 44 of the body 38 to the inner end 42 of the collar 39. The thickness E1 of the upstream arm 47 gradually increases from the downstream end 48 of the upstream portion 44 of the body 38 to the inner end 42 of the collar 39. The inner surface 52 and outer surface 53 of the upstream arm 47 form an acute angle A with each other, defined in the half-section where the cross-sectional plane is longitudinal and passes through the axis X. The acute angle A is approximately 10°.
[0083] like Figure 4 As shown, the downstream arm 49 is a truncated cone shape. The downstream arm 49 expands from downstream to upstream and continuously from the upstream end 50 of the downstream portion 45 of the body 38 to the inner end 42 of the collar 39. More specifically, the inner and outer surfaces 54 of the downstream arm 49 each expand from downstream to upstream and continuously from the upstream end 50 of the downstream portion 45 of the body 38 to the inner end 42 of the collar 39. The thickness E2 of the downstream arm 49 is constant from the upstream end 50 of the downstream portion 45 of the body 38 to the inner end 42 of the collar 39.
[0084] like Figure 4 As shown, the inner surface 52 of the upstream arm 47 and the inner surface 54 of the downstream arm 49 are connected by a fillet 55. Here, the radius R of the fillet 55 is 20 mm.
[0085] The 55-degree radius is defined by center C, which is located at... Figure 4 The center is marked with a cross. The radial dimension Dr between the center C and the inner point P of the downstream end 48 of the upstream portion 44 (or the upstream end 50 of the downstream portion 45) is 14 mm. A fillet 55 forms the bottom of the recess 51, and the fillet 55 is located radially outward relative to the inner end of each of the inner ends of the upstream arm 47 and the downstream arm 49.
[0086] The downstream end 48 of the upstream portion 44 of the main body 38 and the upstream end 50 of the downstream portion 45 of the main body 38 are separated from each other and are axially separated from each other by the recess 51.
[0087] The upstream portion 44 and the downstream portion 45 of the main body 38 are each cylindrical. The upstream portion 44 and the downstream portion 45 of the shaft 11 may each include one or more bearing surfaces on which rolling bearings configured to guide the shaft 11 are mounted.
[0088] The upstream end 63 of the upstream portion 44 and the downstream end 64 of the downstream portion 45 may each include a connecting device (such as a spline) configured to mate with a complementary connecting device.
[0089] like Figure 1 As shown, the upstream end 63 of the upstream portion 44 is directly rotatably connected to the input element 24 of the reducer 23, and the downstream end 64 of the downstream portion 45 is directly rotatably connected to the turbine shaft 16.
[0090] For example, shaft 11 is manufactured by turning.
Claims
1. A compressor shaft (11) for a turbine engine (1) of an aircraft (2), the shaft (11) being integral and annular about a longitudinal axis (X), the shaft (11) comprising a longitudinally extending body (38) and a collar (39) extending substantially radially relative to the axis (X), the collar (39) having an outer end (40) of a bearing flange (41) and an inner end (42) connected to the body (38), the flange (41) being configured to be fixed to a ducted fan (10) and a rotor (7) of a low-pressure compressor (6); Its features are, The body (38) is divided into an upstream portion (44) and a downstream portion (45) that are longitudinally spaced apart from each other. The inner end portion (42) of the collar (39) is connected to the upstream portion and the downstream portion (44, 45) of the body (38) via a fork (46). The fork (46) includes an upstream arm (47) and a downstream arm (49). The upstream arm connects the inner end portion (42) of the collar (39) and the downstream end portion (48) of the upstream portion (44) of the body (38). The downstream arm connects the inner end portion (42) of the collar (39) and the upstream end portion (50) of the downstream portion (45) of the body (38). The upstream arm and the downstream arm (47, 49) form an opening recess (51) on the inside. The upstream arm (47) includes an inner surface (52) that is axially and directly opposite to the inner surface (54) of the downstream arm (49).
2. The shaft (11) according to claim 1, characterized in that, The downstream end (48) of the upstream portion (44) of the main body (38) and the upstream end (50) of the downstream portion (45) of the main body (38) are separated from each other and are axially separated from each other by the recess (51).
3. The shaft (11) according to any one of the preceding claims, characterized in that, The upstream and downstream portions (44, 45) of the main body (38) are each cylindrical.
4. The shaft (11) according to any one of the preceding claims, characterized in that, The recess (51) includes a bottom (55) which is located radially outward relative to the inner ends of each of the inner ends of the upstream arm and the downstream arm (47, 49).
5. The shaft (11) according to any one of the preceding claims, characterized in that, The collar (39) extends in the extension of the downstream arm (49).
6. The shaft (11) according to any one of the preceding claims, characterized in that, The inner and outer surfaces (54) of the downstream arm (49) each expand from downstream to upstream, and expand continuously from the upstream end (50) of the downstream portion (45) of the body (38) to the inner end (42) of the collar (39).
7. The shaft (11) according to any one of the preceding claims, characterized in that, The collar (39) expands from downstream to upstream, from the inner end (42) of the collar to the outer end (40) of the collar.
8. The shaft (11) according to any one of the preceding claims, characterized in that, The inner and outer surfaces (52, 53) of the upstream arm (47) each expand from upstream to downstream, and expand continuously from the downstream end (48) of the upstream portion (44) of the body (38) to the inner end (42) of the collar (39).
9. The shaft (11) according to any one of the preceding claims, characterized in that, The inner and outer surfaces (52, 53) of the upstream arm (47) form an acute angle (A) with each other, the acute angle (A) being defined in a half-section whose cross-sectional plane is longitudinal and passes through the axis (X), preferably, the acute angle (A) being between 5° and 15°.
10. The shaft (11) according to any one of the preceding claims, characterized in that, The maximum radial dimension (D) of the recess (51) is greater than the corresponding maximum radial dimensions (D1, D2) of the upstream portion and the downstream portion (44, 45).
11. A turbine engine (1) for an aircraft (2), the turbine engine comprising: - Gas generator (3), which is supplied with gas by air inlet (4); - Power turbine (5), the power turbine being independent of the gas generator (3); - Low-pressure compressor (6), the low-pressure compressor includes a rotor (7) driven to rotate by the power turbine (5); - A non-ducted fan (8), which is capable of rotational motion and is driven to rotate by the power turbine (5); - Non-ducted flow straightener (9), which is fixed in terms of rotation; - Ducted fan (10), the ducted fan is located in the air inlet (4), the ducted fan (10) is capable of rotational movement and is driven to rotate by the power turbine (5); The rotor (7) of the ducted fan (10) and the low-pressure compressor (6) are jointly driven to rotate by the power turbine (5) via the compressor shaft (11) according to any one of the preceding claims.
12. The turbine engine (1) according to the preceding claim, characterized in that, The ducted fan (10) includes a flange (33), the rotor (7) of the low-pressure compressor (6) includes a drum (17), the drum includes a flange (19), and the flange (33) of the ducted fan (10), the flange (41) of the compressor shaft (11) and the flange (19) of the drum (17) are fixed to each other by an annular bolt (56).
13. The turbine engine (1) according to claim 11 or 12, characterized in that, The non-ducted fan (8) is driven to rotate by the power turbine (5) via a reducer (23).
14. The turbine engine (1) according to the preceding claim, characterized in that, The upstream end (63) of the upstream portion (44) of the compressor shaft (11) is rotatably connected to the input element (24) of the reducer (23), and the non-ducted fan (8) is rotatably connected to the output element (25) of the reducer (23).
15. The turbine engine (1) according to any one of claims 11 to 14, characterized in that, The non-ducted fan (8) includes an annular row of variable pitch blades (21), and the non-ducted flow straightener (9) includes an annular row of variable pitch outlet guide blades (27).