JPH0123660B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION (Industrial Application Field) The present invention relates to a particle separator for removing foreign particles from an inlet air stream of an engine, and more particularly to a particle separator for continuously removing foreign particles from an inlet air stream and substantially discharging foreign particles from an inlet air stream to an engine. The present invention relates to a particle separator that provides a particle-free air stream.

Aircraft engines, especially helicopter engines, are susceptible to damage due to the inhalation of foreign particles such as sand or dust, i.e. when the helicopter is located on or near the ground, the rotors of the helicopter blow air onto the ground; An air flow containing a large amount of sand or dust is generated near the mouth.
This is likely to be inhaled into the engine and cause damage to the engine, in which case a particle separator can be effectively utilized.

(Prior Art) In order to prevent such foreign particles from being introduced into an engine, a particle separation device using inertia has been proposed. The particle separator is coaxially disposed immediately upstream of the engine air inlet opening in a main cover body extending axially forward upstream of the engine and radially extending in the upstream and downstream directions. It is shaped to flare outward. With this inertial particle separator, the air flow containing foreign particles introduced approximately in the axial direction is deflected or changed radially outward, and the foreign particles of sand or dust contained in the air flow are radially removed by inertia. deflected outward. In this case, the foreign particles are forced to move towards the inner surface of the main cover body member, i.e. radially away from the engine space introduction opening, and the relatively particle-free air stream is moved axially in the central part. flow and is routed to the engine's air intake openings. The radially outer airflow containing the deflected particles, on the other hand, travels axially within the main cover body and is introduced into a suitable particle trap.

(Problems to be Solved by the Present Invention) Although the above-mentioned conventional particle separator has a simple operating principle and seems to be effective, when used outdoors, contrary to theory, it is difficult to remove the particles from the introduced air. Particles were not removed so much that satisfactory results could not be obtained. This is thought to be due to the fact that the air flow flowing in the axial direction in the center of the main cover body member contains a relatively large amount of foreign particles.

SUMMARY OF THE INVENTION Accordingly, it is an object of the present invention to provide an inertia-based particle separation device that has greatly improved particle separation and removal functions compared to conventional devices. Therefore, according to the present invention, a particle separator is provided which is capable of removing a large amount of foreign particles such as sand or dust from an air stream introduced into an opening of a gas turbine type engine.

(Means for Solving the Problems) In order to achieve the above-mentioned object, according to the particle separator of the present invention, a particle separator is disposed upstream of the opening of the engine, and the first particle separator of the particle separator A particulate capture section captures a portion of the particles in the inlet air stream, and then a second section of the particle separator directs the remaining portion of the air stream radially away from the engine opening. By configuring the particles to be deflected and moved in separate directions, and both the captured particles and the deflected and moved particles to be continuously discharged into the atmosphere by a fan through an engine bypass path, Realized.

(Function) However, in the particle separator according to the present invention, a considerable amount of foreign particles are removed by the particle separator located in the center of the air flow introduced into the upstream part of the engine, and the air flow flowing through the center Since the foreign particles in the airflow are greatly reduced and the mass is reduced, the airflow can smoothly deflect the remaining foreign particles radially outward, and particle removal can be achieved with high efficiency.

(Embodiment) Referring to the figure, there is shown an upstream section 10 of a gas turbine type engine 12 that drives a main rotor (not shown) of a helicopter, and the upstream section 10 forms an air introduction section to the engine. A hollow, substantially cylindrical cover body 14 is enclosed, and this cover body 1
4 is aligned with the axis 16 of the engine. Further, an air introduction passage 18 is formed at the inlet portion of the cover body member 14, extending along the axial direction of the cover body member 14, and introducing air into the engine. The air introduction passage 18 further has an opening 20 at its inlet that flares outward in the radial direction of the cover body member 14.

The main power shaft 24 of the engine is the air introduction passage 1
8, and the left end of the main power shaft 24 is connected to a gear box 26 disposed slightly upstream of the opening 20.
It is operatively connected to a drive shaft 28 that extends in the axial direction through. The rotational force of the drive shaft 28 is transmitted to the rotor of the helicopter. A group of blades 30 are provided within the air introduction passage 18 and spaced apart from each other along the outer peripheral surface of the main power shaft 24, and the blades 30 define a compressor portion that constitutes a first component of the engine. Other components of the engine (eg, combustor components and turbine components) are not shown but are arranged downstream of the vanes 30 in a known manner.

Especially when the helicopter is located on or near the ground, the air flow blown toward the ground by the rotor causes a large amount of air flow 32 containing sand or dust to flow into the vicinity of the engine opening 20. If the air flow 32 containing a large amount of particles such as sand or dust is introduced into the engine through the opening 20, it is undesirable because the durability of the internal parts of the engine will be greatly impaired. A unique inertial particle separation device 34 is provided. The inertial particle separation device 34 of the present invention includes a hollow, substantially cylindrical main cover body member 35 into which air is introduced, and the upstream portion 10 of the engine is coaxially disposed inside the main cover body member 35. The main cover body member 35 extends upstream and downstream of the opening 20 . Opening 2 by main cover body member 35
An introduction air passage 36 that communicates with the opening 20 and immediately upstream of the air passage 20 is defined along the axial direction. As also shown, the air inlet passageway 36 has a radially outwardly extending opening 38 at its upstream end, the diameter of the opening 38 being slightly larger than the diameter of the upstream end portion 22 of the engine 12. . The air introduction path 36 is an opening 38
It is formed into a flared shape so as to slightly expand outward in the radial direction along its longitudinal direction.

The cover body member 14, the upstream end portion 10, and the main cover body member 35 define an annular bypass passage 40 that communicates with the air introduction passage 36. The downstream end of the bypass passage 40 communicates with an annular collection chamber 42 defined within the main cover body member 35 .

Inertial particle separator 34 also includes a hollow, generally spherical inertial particle separator 44 . An inertial particle separator 44 is disposed upright upstream of the opening 20, and portions of the shafts 24, 28 adjacent to the gear box 26 and the gear box 26 are rotatably passed through the inertial particle separator 44. The upstream portion 46 and downstream portion 48 of the inertial particle separator 44 are configured to face the downstream direction and flare radially outward, and to face the downstream direction and flare radially inward, respectively.

The inertial particle separator 44 is partially protruded into the inlet air passage 18, and the downstream part 48 of the inertial particle separator 44 is
The cover body member 14 is attached to the cover body member 14 through a group of supporting plates 50 that are equally spaced in the circumferential direction of the opening 20 and extend substantially radially. By arranging the downstream section 48 in the inertial particle separator 44 as described above, the downstream section 48 closes off the central portion of the opening 20 and the downstream section 48 and the inner surface of the cover body 14 form an annular inlet passage 52 . are divided. The inlet passage 52 is located between the inlet air passages 36 and 18 and flares outward in the radial direction toward the upstream direction.

The drive shaft 28 is housed within a hollow housing 54 that is tapered in an upstream direction and abuts the upstream end 56 of the inertial particle separator 44 . On the other hand, inertial particle separator 4
4 is provided with an annular particle trap 58 which extends generally axially and has an inlet portion 60 which flares radially outward in the upstream direction. The interior of the particle trap 58 includes a group of ducts 62 circumferentially spaced from its downstream end.
It is communicated with the bypass path 40 via. This duct 62 passes through the interior of the inertial particle separator 44 and extends through the inlet channel 52 between the support plates 50 as well as through the wall of the cover body 14 to the bypass channel 40 .

The inertial particle separator 34 further includes a fan 64 (shown schematically) for removing particles, the inlet and outlet of the fan 64 being connected to an inlet duct 66, respectively.
and a discharge duct 68. The other end of the inlet duct 66 communicates with the annular collection chamber 42, and the other end of the discharge duct 68 is open to the atmosphere. The inertial particle separator 44 and the fan 64 preferably cooperate to continuously remove foreign particles from the air stream 32 introduced into the engine and discharge it to the atmosphere substantially free of foreign particles. Airflow can be reliably supplied to the engine.

Next, the operation of the inertial particle separation device will be explained. When the gas turbine type engine 12 and the fan 64 are driven, an air flow 3 containing foreign particles is generated.
2 is introduced into the opening 20 from the opening 38 through the air introduction path 36. At this time, the inertial particle separator 44 disposed between the openings 20 and 38 acts to capture some of the foreign particles contained in the air flow 32, and the foreign particles that are not captured are removed from the engine. 12 radially outwardly, ie, to the outer periphery of the air inlet passageway, so that foreign particles can be substantially completely removed from the airflow directed to the engine. Both the captured foreign particles and the foreign particles moved radially outward are continuously discharged by the fan 64 to the atmosphere through the engine bypass path.

More specifically, when a particle-laden airflow 32 is introduced into the engine 12 via the air introduction passage 36, the airflow 32 first impinges on the upstream portion 46 of the inertial particle separator 44 and the adjacent housing 54. . A portion of this particle and a portion 3 of the air stream 32
2a, the collection chamber 42 is rotated by the rotation of the fan 64.
Since the inside of the particle trapping section 58 is under negative pressure through the duct 62, the particles are sucked into the particle trapping section 58.

Since the upstream portion 46 of the inertial particle separator 44 is expanded radially outward, the remaining foreign particles are directed radially outward toward the inner surface of the main cover body member 35, and at this time, the particle trap 58 radially outward inertia is imparted to foreign particles that are not captured. As a result, the air flows 32a, 32b contain most of the particles, and the air flows 32a, 32b directed radially outward are separated from the air flows 32c, which are substantially free of particles, radially inward.

Since the interior of the collection chamber 42 is maintained at a negative pressure state by the fan 64, the air flow 32b directed radially outward and the air flow 32a introduced into the particle trap 58 pass through the bypass passage 40 to the collection chamber 42. The fans 64 cause the particles contained in the air streams 32a, 32b to be discharged from the collection chamber to the atmosphere. Accordingly, in the present invention, engine bypass or particle trap 58, duct 62, bypass passage 40, collection chamber 42,
A continuous discharge of foreign particles will take place via the inlet duct 66 and the discharge duct 68.

On the other hand, the air flow 32c is substantially free of foreign particles.
is introduced into the inlet passage 52 by the rotation of the vane 30,
Furthermore, it is continuously supplied to a gas turbine type engine 12. At this time, the amount of particles contained in the air flow 32c is greatly reduced compared to the amount of particles contained in the air introduced into the engine by a conventional inertial particle separator, and the deterioration of internal parts due to particles introduced into the engine is significantly reduced. be done.

In particular, according to the present invention, particle separation performance can be greatly improved by suitably cooperating the particle trapping section 58 and the fan 64. The air flow 32 introduced into the air introduction channel 36 does not flow completely along the axis 16 at the flared opening 38 of the air introduction channel 36 , but rather along a direction substantially oblique to the axis 16 . Since it is introduced, the main cover body member 35
The air flow introduction efficiency can be increased.

By introducing the air stream 32 in a direction oblique to the axis rather than completely along the axis, the inertial particle separator 44 allows the air stream 32 to
It will be appreciated that the angle at which the desired separation inertia force is imparted to the particles contained in 2 can be greatly increased.

That is, many conventional devices that remove particles by simply deflecting the airflow are unable to sufficiently deflect the entire incoming airflow, especially when the airflow 32 contains a large amount of sand or dust. Although a considerable amount of foreign particles have been introduced into the engine, according to the present invention, the introduction of the air flow 32 from the opening 38 is prevented, especially since the particle trap 58 extends radially inward of the opening 20. At times, a significant amount of particles may be removed and the airflow may be deflected radially outwardly by the inertial particle separator 44, i.e., the airflow 32 may be directed such that the inlet portion 60 of the particle trap 58 is at an angle to the axis 16. Since the particle trapping section 58 is configured in a flared shape for introduction, the particle trapping efficiency of the particle trapping section 58 is improved. In addition, in this way, the particle trapping section 58
This removes a significant amount of particles from the air stream at the time of introduction, reducing the amount of particles, greatly increasing the air flow deflection capability of the inertial particle separator compared to conventional products, resulting in a The air stream 32c directed to is substantially free of foreign particles.

It will be understood that the invention is not limited to the embodiments shown, but encompasses modifications within the scope of the claims.

(Effects of the Invention) According to the present invention configured as described above, foreign particles can be continuously removed from the air flow introduced into the engine, and since there is substantially no inflow of foreign particles into the engine, the engine It can greatly improve the durability of.

Embodiments of the invention are summarized below.

1. Placing a particle separator in the flow path for the air flow containing particles to be delivered to the inlet opening of the engine; a capture/deflection step in which the remainder of the particles contained in the airflow are deflected and moved radially outward of the air flow; and a discharge step in which the particles are continuously released into the atmosphere via a bypass path that bypasses the inlet opening. A method for removing particles from an inlet air stream directed to an inlet opening of an engine comprising:

2. The method of claim 1, wherein the discharging step is carried out by directing the particles to a downstream portion of the inlet opening and discharging them through a fan.

3. A particle separator and an inlet are provided by a cover body member device that defines an inlet air passage communicating with the inlet opening, a recovery chamber disposed downstream of the inlet opening, and a bypass passage extending between the inlet air passage and the recovery chamber. The step of surrounding the opening further includes the step of surrounding the opening, the step of capturing and deflecting includes the step of forming a particle trap upstream of the particle separator, and the step of discharging includes the step of surrounding the particle trap and the bypass path. The first step includes the step of extending the duct.
The method described in section.

4. The method according to item 3 above, wherein the discharge step includes the step of linking the fan with the collection chamber.

5. The discharge step includes moving a portion of the particles along a channel disposed at least partially radially inside the inlet opening and at least partially disposed radially outside the inlet opening. 2. The method according to item 1, further comprising the step of moving the remainder of the particles along the flow path.

6 Dividing the airflow introduced into the gas turbine type engine through the inlet opening into a first and second airflow, moving the first airflow upstream of the inlet opening and radially inward of the inlet opening. moving the second air stream radially outwardly of the inlet opening so that the first and second air streams contain substantially all of the particles of the incoming air stream; a bypass step of directing an air flow into a bypass path of the inlet opening; and a step of directing a third air flow excluding the first and second air flows of the inlet air flow into the inlet opening. A method of preventing damage to the present invention by particles contained in an air stream introduced into the inlet opening of an engine.

7. The method according to item 6 above, wherein the flow dividing step includes a step of arranging an inertial particle separator in the introduction air path.

8 The diversion step includes forming a trap in the inertial separator to trap a portion of the particles in the inlet air stream, and the bypass step includes connecting a duct to the trap and the engine inlet. 8. The method of claim 7, further comprising the step of extending the duct to a location downstream from the opening.

9. The method of item 8, wherein the bypass step further includes the step of collecting the first and second divided air streams with a fan and continuously discharging them to the atmosphere.

[Brief explanation of drawings]

The figure is a sectional view of the upstream part of a gas turbine engine equipped with an inertial particle separation device according to the present invention. DESCRIPTION OF SYMBOLS 10... Upstream part, 12... Gas turbine engine, 14... Cover body member, 16... Axis line, 18
... Air introduction path, 20 ... Opening, 22 ... Upstream end, 24 ... Main power shaft, 26 ... Gear box, 28 ... Drive shaft, 30 ... Vane, 3
2, 32a, 32b, 32c... air flow, 34...
...Inertial particle separator, 35...Main cover body member,
36...Introduction air path, 38...Opening, 40...
Bypass path, 42... Recovery chamber, 44... Inertial particle separator, 46... Upstream section, 48... Downstream section, 50... Support plate, 52... Inlet section, 54...
Housing, 56...upstream end, 58...particle trapping section, 60...inlet section, 62...duct, 64...
... Juan, 66... Inlet duct, 68... Outlet duct.

Claims (1)

[Scope of Claims] 1. A wall device delimiting an axially extending inlet air passage for receiving a particle-laden inlet air stream and supplying it to an inlet opening of a gas turbine type engine, and an inlet in the inlet air passage. A trapping device disposed upstream of the opening that captures a portion of the particles from the airflow flowing through the inlet airway, and a deflection device that deflects and moves the remainder of the particles radially outward from the airflow flowing through the inlet airway. an inertial particle separator for removing particles from the airflow flowing through the inlet air passage; and an inertial particle separator for removing particles from the air flow flowing through the inlet air passage; and a particle emitting device for continuously discharging particles into a gas turbine type engine. 2. The inertial particle separator has an upstream section including a deflection device, the capture device has a particle capture section disposed in the upstream section, and the particle ejection device downstream of the inlet opening separates the captured particles and the deflected particles. A particle separator according to claim 1, comprising a device for collecting collected particles and a fan device for releasing the collected particles into the atmosphere. 3. A patent claim in which the particle emitting device includes a duct device through which the trapping device extends and bypasses the inlet opening, and a fan device linked to the engine and introducing the captured particles through the duct device and releasing them to the atmosphere. The particle separator according to item 1. 4. Particles according to claim 3, wherein the trapping device includes a particle trapping part having an annular opening coaxial with the axis and flaring radially outward in the upstream direction. Separation device. 5 The wall device defines a bypass path communicating with the inlet air path and extending downstream from the inlet opening, and a collection chamber communicating with the bypass path and extending downstream from the bypass path, and the particle emitting device is connected to the trapping device and the bypass path. 2. A particle separator as claimed in claim 1, comprising a duct system extending therebetween and a fan having an inlet communicating with the collection chamber. 6 An inlet air passage that coaxially surrounds the upstream part of the gas turbine type engine and communicates with the inlet opening that receives the inlet air flow and extends upstream from the inlet opening; a cover body member extending downstream from the inlet opening and defining an annular bypass passage for receiving deflected and transferred particles; An annular trapping part that traps particles contained in the airflow flowing through the introduction air passage; and a radial direction that extends downstream from the trapping part and deflects particles contained in the airflow flowing through the introduction air passage radially outward. an inertial particle separator having a flare section configured to flare outward; at least one duct communicating the trapping section with the bypass passage; and an inertial particle separator connected to the bypass passage and continuously transporting particles from the bypass passage through the duct. A particle separation device for removing particles from an inlet air stream directed to a gas turbine engine having a discharge fan. 7. The particle separator according to claim 6, wherein an annular recovery chamber communicating with the bypass path is defined downstream of the bypass path by the cover body member, and an inlet portion of the fan communicates with the recovery chamber. 8. The particle separator according to claim 6, wherein the inertial particle separator is hollow and the duct is installed inside the inertial particle separator. 9. The particle separator according to claim 8, wherein the duct extends radially inward through the inlet opening of the engine. 10. A particle separator according to claim 6, wherein the annular inlet opening of the trap faces upstream and flares radially outward. 11 each comprising a group of circumferentially spaced ducts connected at one end to the catch via a connection and extending from the connection through the interior of the catch and into the engine inlet opening and into the bypass passage; A particle separator according to claim 6, which comprises: