JP3711028B2 - Gas turbine engine with foreign matter removal structure - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention is a gas turbine engine mainly used as a power source of an aircraft such as a helicopter, a drive source of a generator, and the like, and easily collects and removes foreign matter that has entered the engine with a simple configuration. It is related with the thing provided with the foreign substance removal structure which can do.
[0002]
[Prior art]
In a gas turbine engine used for the above-described applications, foreign matters such as sand, pebbles, metal pieces or twigs are likely to enter the engine in a state where they are contained in the intake air. If it collides with a turbine blade, the engine may be damaged due to damage caused by the impact received during the collision. In particular, in an engine having ceramic turbine blades that are brittle against impacts, even fine foreign matters that have not been a problem in the past are damaged and cause failure. That is, in an engine equipped with ceramic turbine blades, not only foreign matters contained in the intake air but also foreign matters such as cutting powder and carbon lump generated inside cause damage.
[0003]
Therefore, conventionally, the inhaled air is swirled or passed through a curved passage, and then introduced into the engine so that foreign matter heavier than air is led out in the direction away from the air flow path by centrifugal force. IPS (inlet particle separator) that removes the air and sucks only air into the engine is widely used.
[0004]
[Problems to be solved by the invention]
However, with the conventional foreign matter removing means (IPS), it is difficult to prevent foreign matter having a small weight from entering the engine, and it is impossible to remove foreign matter that has once entered the engine. Further, with a conventional means such as IPS, the collected foreign matter cannot be taken out until the engine is disassembled at the time of periodic inspection.
[0005]
Therefore, the present invention has been made in view of the above-described conventional problems, and a foreign matter removal structure can be provided in a compact and inexpensive manner using existing parts in the engine, and the collected foreign matter can be arbitrarily selected. An object of the present invention is to provide a gas turbine engine that can be taken out.
[0006]
[Means for Solving the Problems]
In order to achieve the above object, a gas turbine engine according to a first configuration of the present invention is configured such that the air from the diffuser is directed downstream in the axial direction from the radially outward to the downstream of the diffuser of the centrifugal compressor in the gas turbine engine. curved path to be diverted radially inward through is formed, radially outer peripheral portion of the curved path, the collection port to derive the said curved path outside by entering the foreign matter in the air is formed .
[0007]
According to this configuration, since the air discharged from the diffuser flows with a swirling component, the foreign matter contained in the air resists the centrifugal force due to the swirling of air and the bending of the curved passage. And inertial force to flow. For this reason, air forcibly flows along the curved passage, whereas foreign substances heavier than air act from large centrifugal force and inertial force, so that they come out of the curved passage and enter the collection port. Removed from the air. In general, the curved passage downstream of the centrifugal compressor has a relatively large bending angle, so that the effect of collecting foreign matter by the inertial force acting on it is extremely large, and even small foreign matter is almost certainly collected. Can do. Further, this foreign matter removing structure is different from the conventional foreign matter removing means in which the flow path is bent to be particularly large for removing the foreign matter, and the existing curved passage is used to form the outer circumferential portion of the curved passage. Since it is only necessary to provide a collection port, it can be made compact and does not cause an increase in cost.
[0008]
A gas turbine engine according to a second configuration of the present invention includes an inner cylinder in which a combustor in the gas turbine engine forms a combustion chamber, an outer cylinder that covers an outer peripheral portion and a top part of the inner cylinder, and the inner cylinder and the outer cylinder. Between the top wall and the peripheral wall of the outer cylinder, and an introduction passage that introduces air from the compressor in a direction opposite to the flow direction of the combustion gas in the inner cylinder. In addition, a collection port for allowing foreign matter in the air to enter and leading out of the introduction passage is formed.
[0009]
According to this configuration, since the compressed air flowing through the introduction passage has a swirling component, foreign matter contained in the compressed air is caused by centrifugal force due to swirling and the top wall of the outer cylinder. Inertial force generated by turning to a right angle acts. Therefore, the foreign matter is separated from the compressed air and enters the collection port and is collected. In addition, this foreign matter removing structure can be provided by using an existing introduction passage without bending the compressed air flow path to a large extent, and merely providing a collection port at the boundary portion outside the abutting portion of the introduction passage. Since it is good, it can be configured compactly and does not cause an increase in cost.
[0012]
In the first and second configurations, the collection port is preferably formed in an annular shape that is concentric with the shaft center of the engine, whereby foreign objects can be collected over the entire circumference of the air passage.
[0013]
In the first and second configurations, it is preferable that an outlet for taking out the collected foreign matter to the outside of the engine and a plug for opening and closing the outlet are provided. As a result, the collected foreign matter can be discharged to the outside simply by opening the outlet with the plug without disassembling the engine.
[0014]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the drawings.
FIG. 1 is a longitudinal sectional view showing a schematic configuration of a gas turbine engine provided with a foreign matter removing structure according to a first embodiment of the present invention.
[0015]
This gas turbine engine includes a two-stage centrifugal compressor 1 that sucks and compresses air A from an air inlet IN, a combustor 4 that supplies fuel to the compressed air A for combustion, and a combustion gas G. And a turbine 7 to be driven. The compressor 1 and the turbine 7 are accommodated in a housing 13, and the combustor 4 protrudes from the housing 13. The combustion gas G generated in the combustion chamber C of the combustor 4 is guided to the turbine 7 via the scroll 9 to rotate the turbine 7, and the two-stage centrifugal compressor connected to the turbine 7 by the rotating shaft 10. 1 and a rotational load L such as a generator or helicopter rotor.
[0016]
The combustor 4 is a single can type (may be a multi-can type), and is provided so as to protrude in a substantially radial direction of the turbine 7. The combustor 4 includes an inner cylinder 8 that forms a combustion chamber C, and an outer cylinder 11 that covers the outer peripheral portion 8a and the top 8b of the inner cylinder 8, and between the inner cylinder 8 and the outer cylinder 11, An introduction passage 12 for introducing the compressed air CA from the compressor 1 in the direction opposite to the flow direction of the combustion gas G in the inner cylinder 8 is formed. The compressed air CA supplied from the compressor 1 flows in the introduction passage 12 toward the tip side of the combustor 4, is turned toward the center side of the combustor 4 and enters the inner cylinder 8, and the inner cylinder mixed with fuel nozzle or we supplied fuel burned After a combustion gas G in the 8, it flows toward the base end side of the combustor 4. The two compression stages 2 and 3 constituting the centrifugal compressor 1 are fixed to the rotating impeller rotors 2a and 3a and the housing 13 on the downstream side thereof to suppress the swirling of the air A and convert the dynamic pressure to static pressure. And diffusers 2b and 3b for increasing the static pressure.
[0017]
Between the discharge port 2ex of the first compression stage 2, that is, the downstream end of the diffuser 2b, and the suction port 3in of the second compression stage 3, that is, between the suction end of the impeller rotor 3a, the diffuser 2b A curved passage 14 is formed for turning the air A so as to make a U-turn from the radially outward direction of the gas turbine engine to the radially inward direction.
[0018]
As shown in FIG. 2, which is an enlarged view of a portion II in FIG. 1, foreign matter E in the air A is caused to enter the engine housing 13 that forms the radially outer peripheral portion of the curved passage 14 to the outside of the curved passage 14. The collection port 17 to be led out is formed in an annular shape concentric with the shaft center of the rotating shaft 10 (FIG. 1), that is, the shaft center 25 of the gas turbine engine. A collection chamber 18 is provided. Further, the collection chamber 18 is formed with an outlet 19 formed of a screw hole communicating with the outside, and a plug 20 made of a bolt is detachably screwed into the outlet 19. A plurality of outlets 19 that are opened and closed by the attachment and detachment of the plug 20 may be formed in the circumferential direction, or only one may be provided at the lower part of the annular collection chamber 18 as shown in FIG.
[0019]
In general, the air A discharged from the diffuser 2b flows with a swirling component. Therefore, if the foreign matter E is included in the air A, the foreign matter E is centrifuged by the swirling of the air A. Force and inertial force due to bending along the curved path 14 are applied. Therefore, the foreign matter E heavier than the air A moves radially outward from the curved passage 14, enters the collection port 17 in FIG. 2, and is stored in the collection chamber 18.
[0020]
In the foreign matter removing structure, since the bending angle of the curved passage 14 is as large as about 180 °, the effect of collecting the foreign matter E by inertia force is extremely large, and even in the small foreign matter E, the inside of the collecting chamber 18 is almost certainly obtained. Can be collected. Further, this foreign matter removing structure is different from the conventional foreign matter removing means that bends the flow path particularly greatly, and has a collecting port 17 in the radially outer peripheral portion of the curved passage 14 using the existing curved passage 14. Since only the collection chamber 18 needs to be provided, it can be configured in a compact manner and the cost is not increased.
[0021]
In addition, the foreign matter E stored in the collection chamber 18 can be naturally dropped from the outlet 19 to the outside if the lower plug 20 shown in FIG. 1 is removed when the engine is stopped. During driving of the engine, even if the upper plug 20 is removed, it can be blown off toward the outlet 19 by air pressure and discharged to the outside. Note that if the outlet 19 can be automatically opened and closed by a solenoid valve or the like instead of the plug 20, it can be easily opened even during operation of the engine and foreign matter can be discharged.
[0022]
FIG. 3 is an enlarged view of a portion III in FIG. 1, and the air A from the diffuser 3b is introduced into the discharge port 3ex of the second compression stage 3 from the radially outward direction of the gas turbine engine to the axial direction of the engine. A curved passage 21 is formed to turn rearwardly (to the right in the figure).
[0023]
The engine housing 13 forming the radially outer peripheral portion of the curved passage 21 has a collection port 22 through which foreign matter E in the air A enters and leads out of the curved passage 21, and is a shaft of the rotary shaft 10 (FIG. 1). It is formed in an annular shape concentric with the core 25, and a collection chamber 23 for foreign matter E is provided at the back of the collection port 22. Further, the collection chamber 23 is formed with an outlet 24 made of a screw hole communicating with the outside, and a plug 27 made of a bolt is detachably screwed into the outlet 24. A plurality of outlets 24 that are opened and closed by attaching and detaching the plug 27 may be formed in the circumferential direction, or only one may be provided in the lower part of the annular collection chamber 23 as shown in FIG.
[0024]
In this foreign matter removing structure, substantially the same effect as the structure of FIG. 2 can be obtained. That is, the foreign matter E contained in the air A receives the centrifugal force due to the swirling of the air A and the inertial force due to the bending along the curved passage 21, and is collected from the curved passage 21 outward in the radial direction. It enters into the mouth 22 and is stored in the collection chamber 23. Also in this foreign matter removing structure, since the bending angle of the curved passage 21 is relatively large at about 90 °, the effect of collecting the foreign matter E by inertia force is great, and even the small foreign matter E is almost certainly collected. Can be collected inside.
[0025]
FIG. 4 shows a foreign matter removal structure according to a modification of the first embodiment of the present invention. This foreign matter removing structure is applied to a gas turbine engine equipped with the two-stage centrifugal compressor 1 shown in FIG. 1, and instead of the collection chamber 18 of FIG. An existing sealed space formed therebetween is used as the collection chamber 28. The collection chamber 28 is an annular space concentric with the engine shaft 25 (FIG. 1). A collection passage 30 communicating with the collection chamber 28 having a collection port 29 through which foreign matter E in the air A enters and leads out of the curved passage 14 is rotated at the outer periphery in the radial direction of the curved passage 14. It is formed in an annular shape concentric with the shaft center 25 (FIG. 1) of the shaft 10. Between the collection passage 30 and the collection chamber 28, there is formed an outlet 31 made of a screw hole communicating with the outside, and a plug 32 made of a bolt is detachably screwed into the outlet 31. Has been. A plurality of outlets 31 may be formed in the circumferential direction, or only one outlet 31 may be provided in the lower part of the annular collection chamber 28.
[0026]
Since this foreign matter removing structure has substantially the same structure as that shown in FIG. 2, it operates in the same manner as described with reference to the structure shown in FIG. That is, the foreign substance E contained in the air A receives the centrifugal force due to the swirling of the air A and the inertial force due to the bending of the curved passage 14, and comes off radially outward from the curved passage 14 and the collection port 29. After entering the interior, it is stored in the collection chamber 28 through the collection passage 30.
[0027]
In addition, this foreign matter removing structure uses an existing curved passage 14 and a sealed space between both compression stages 2 and 3 of the centrifugal compressor 1, and a collection port 29 is provided at the radially outer peripheral portion of the curved passage 14. Since it is only necessary to provide the collecting passage 30, it can be made compact and does not cause an increase in cost. Further, the foreign matter E stored in the collection chamber 28 is removed by air pressure if a lower plug (not shown) is removed when the engine is stopped or if any plug 32 is removed while the engine is running. 31 can be discharged to the outside. In addition, since this foreign material removal structure is equipped with the collection chamber 28 with a large volume, there also exists an advantage which can reduce the discharge frequency of the foreign material E in storage.
[0028]
FIG. 5 is a longitudinal cross-sectional view showing a main configuration of a gas turbine engine having a foreign matter removing structure according to a second embodiment of the present invention. This foreign matter removing structure is provided in the combustor 4 of the gas turbine engine shown in FIG. 1, and the same or equivalent parts as those in FIG. A swirler 34 is attached to the top 8 b of the inner cylinder 8 of the combustor 4 in FIG. 1 so as to surround the fuel nozzle 13, and the compressed air CA from the centrifugal compressor 1 passes through the introduction passage 12 and is one of them. The part flows into the combustion chamber C from the air hole 33 for combustion or dilution of the inner cylinder 8, and the other part makes a U-turn from the introduction passage 12 and turns inside by passing through the swirler 34. Flow into.
[0029]
In the foreign matter removing structure of this embodiment, the collection port 39 through which the foreign matter E contained in the compressed air CA enters the boundary portion between the top wall 37 and the peripheral wall 38 of the outer cylinder 11 and leads out of the introduction passage 12 is provided. The collection chamber 40 is provided in the peripheral wall 38 that is formed and corresponds to the inner part of the collection port 39. Further, the collection chamber 40 is formed with an outlet 41 formed of a screw hole communicating with the lower outside, and a plug 42 formed of a bolt is detachably screwed into the outlet 41.
[0030]
In general, the compressed air CA flowing in the introduction passage 12 has a swirling component added by the compressor 1, and therefore, if the foreign air E is included in the compressed air CA, The centrifugal force due to the turning and the inertial force generated by being changed to a right angle by the top wall 37 of the outer cylinder 11 act. Therefore, the foreign matter E heavier than the compressed air CA is separated from the compressed air CA, enters the collection port 39, and is stored in the collection chamber 40.
[0031]
In the foreign matter removing structure, since both the inertial force and the turning force acting on the foreign matter E are large, even the small foreign matter E is almost certainly led out of the introduction passage 12 from the collection port 39 and inside the collection chamber 40. Can be collected. Further, this foreign matter removing structure is different from the conventional foreign matter removing means that bends the flow path particularly greatly, and uses the existing introduction passage 12 to capture the boundary portion outside the abutting portion of the introduction passage 12. Since it is only necessary to provide the collection chamber 40 having the collection port 39, it can be made compact, and the cost is not increased.
[0032]
The foreign matter E stored in the collection chamber 40 can be discharged from the outlet 41 by removing the plug 42 when the engine is stopped or driven. Further, when the engine is stopped, it is easy to remove the foreign matter E by removing the top wall 37. In this foreign matter removal structure, as shown by a two-dot chain line, if a guide recess 43 having a concave cross-sectional shape is formed on the inner side in the radial direction of the collection port 39 on the lower surface of the top wall 37, the compressed air CA The foreign matter E inside can be smoothly guided into the collection port 39.
[0033]
FIG. 6 is a partially broken side view showing a schematic configuration of a gas turbine engine including a foreign matter removing structure according to a reference example not included in the present invention. First, the configuration of this gas turbine engine will be briefly described.
[0034]
This gas turbine engine compresses air A with an axial flow compressor 44 and guides it to a combustor 47, and injects and burns gas fuel or liquid fuel into the combustor 47, and the high-temperature and high-pressure combustion gas G The turbine 48 is driven. The axial flow compressor 44 includes a plurality of moving blades 50 attached to the outer periphery of the rotary shaft 49 and a plurality of compressors on the inner peripheral surface of the compressor shroud 51 that forms the outer peripheral wall of the air passage 67 of the axial flow compressor 44. The air A sucked from the intake duct 53 is compressed by a combination with the stationary blades 52 arranged in stages, and the compressed air CA is supplied to the annularly formed vehicle compartment 54.
[0035]
A plurality of (for example, six) combustors 47 are arranged in the annular casing 54 along the circumferential direction at equal intervals. The compressed air CA supplied to the casing 54 is indicated by arrows a, As shown by b, it passes through the substantially cylindrical outer cylinder 56 and is guided to the combustion chamber 58 in the substantially cylindrical inner cylinder 57. On the other hand, fuel F is injected into the combustor 47 from the fuel nozzle 59 into the combustion chamber 58, the fuel F is mixed with the compressed air CA and burned, and the high-temperature and high-pressure combustion gas G is downstream of the inner cylinder 57. It is sent to the turbine 48 through a transfer duct 60 connected to the side.
[0036]
FIG. 7 is an enlarged view of a portion VII in FIG. 6 and shows the foreign matter removing structure of the gas turbine engine. This foreign matter removing structure is a collection port through which foreign matter E in the air A enters the compressor shroud 51 and leads out of the air passage 67 at a location near the rear of the moving blade 50 in the final stage of the axial compressor 44. 61 is formed in an annular shape that is concentric with the axis of the rotating shaft 49, that is, the axis 25 (FIG. 6) of the gas turbine engine, and a collection chamber 62 for foreign matter E is provided at the back of the collection port 61. It has been. Further, the collection chamber 62 is formed with an outlet 63 made of a screw hole communicating with the outside, and a plug 64 made of a bolt is detachably screwed into the outlet 63. A plurality of outlets 63 that are opened and closed by attaching and detaching the plug 64 may be formed in the circumferential direction, or only one may be provided in the lower part of the annular collection chamber 62 as shown in FIG.
[0037]
In the axial flow compressor 44, since the air A is swirled by the moving blade 50, if the foreign matter E is contained in the air A, centrifugal force due to the swirling acts on the foreign matter E. Therefore, the air A flows along the air passage 67, but the foreign matter E heavier than the air A is collected by separating from the air passage 67 radially outward because a relatively large centrifugal force acts. It enters into the mouth 61 and is stored in the collection chamber 62.
[0038]
In addition, this foreign matter removing structure is only required to provide the collection chamber 62 having the collection port 61 in a part of the existing compressor shroud 51, so that it can be made compact and does not cause an increase in cost.
[0039]
Furthermore, the foreign matter E stored in the collection chamber 62 can be naturally discharged from the outlet 63 and discharged by removing the lower plug 64 shown in FIG. 6 when the engine is stopped. If one of the plugs 54 is removed while the engine is running, it can be blown off toward the outlet 63 by air pressure and discharged to the outside.
[0040]
【The invention's effect】
As described above, according to the gas turbine engine of the present invention, the existing curved passage connected downstream of the diffuser of the centrifugal compressor, the existing outer cylinder in the combustor, or the existing compressor shroud in the axial compressor In addition, because it has a configuration that has a collection port that allows foreign matter contained in the air to enter using the turning force and inertial force, it is a compact foreign matter that uses existing parts in the gas turbine engine. The removal structure can be configured at low cost.
[Brief description of the drawings]
FIG. 1 is a longitudinal sectional view showing a schematic configuration of a gas turbine engine provided with a foreign matter removing structure according to a first embodiment of the present invention.
FIG. 2 is an enlarged view of a portion II in FIG.
FIG. 3 is an enlarged view of part III in FIG.
FIG. 4 is a longitudinal sectional view showing a main configuration of a gas turbine engine provided with a foreign matter removing structure according to a modification according to the embodiment;
FIG. 5 is a longitudinal sectional view showing a main configuration of a gas turbine engine provided with a foreign matter removing structure according to a second embodiment of the present invention.
FIG. 6 is a partially cutaway side view showing a schematic configuration of a gas turbine engine having a foreign matter removing structure according to a reference example not included in the present invention.
7 is an enlarged view of a portion VII in FIG. 6. FIG.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Centrifugal compressor, 2b, 3b ... Diffuser, 4, 47, 58 ... Combustor, 8 ... Inner cylinder, 11 ... Outer cylinder, 12 ... Introduction passage, 14, 21 ... Curved passage, 17, 22, 29, 39 , 61 ... Collection port, 19, 24, 41, 63 ... Take-out port, 20, 27, 42, 64 ... Plug, 25 ... Axle, 37 ... Top wall, 38 ... Circumferential wall, 44 ... Axial flow compressor, 51 ... compressor shroud, 58 ... combustion chamber, 67 ... air passage, A ... air, E ... foreign matter, C ... combustion chamber.

Claims (4)

Downstream of the diffuser of a centrifugal compressor in a gas turbine engine, a curved path to be deflected inwardly air in the radial direction from the outward axial direction in the radial direction through the backward from the diffuser is formed,
A gas turbine engine in which a collection port through which foreign matter in the air enters and leads out of the curved passage is formed in a radially outer peripheral portion of the curved passage . A combustor in a gas turbine engine is formed between an inner cylinder that forms a combustion chamber, an outer cylinder that covers an outer peripheral portion and a top part of the inner cylinder, and the inner cylinder and the outer cylinder. An introduction passage for introducing the combustion gas in the inner cylinder in a direction opposite to the flow direction;
A gas turbine engine in which a foreign substance in the air is allowed to enter a boundary portion between a top wall and a peripheral wall of the outer cylinder and led out of the introduction passage. 3. The gas turbine engine according to claim 1 , wherein the collection port is formed in an annular shape concentric with an engine shaft center. In any one of claims 1 3, further comprising: a takeout retrieving the collected foreign substances to the outside of the engine, a gas turbine engine and a plug for opening and closing the outlet.

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