JP5724258B2 - Gas turbine engine - Google Patents

Description

  The present invention relates to a gas turbine engine.

  In a gas turbine engine such as a jet engine, air compressed in a compressor is sent to a combustor, and a high-temperature gas is generated by burning a mixture of compressed air and fuel in the combustor, and the turbine is driven by the high-temperature gas. doing.

  Such a compressor of a gas turbine engine is fixed to a casing or the like and is not rotationally driven, but a stationary blade row in which a plurality of stationary blades that rectify air is arranged around the shaft, and is fixed to the shaft and rotationally driven. A plurality of moving blade rows in which a plurality of moving blades are arranged are alternately provided, and air is compressed by alternately passing the stationary blade rows and the moving blade rows.

JP 2009-52546 A

By the way, the flow path (core flow path) in which the stationary blades and the moving blades of the compressor are arranged is very narrow compared to the air intake port from the outside to the gas turbine engine. For this reason, the air taken in from the intake port is accelerated in the core flow path and passes through the stationary blade and the moving blade. The flow velocity of the air passing through the stationary blade and the moving blade is proportional to the air flow rate.
Here, as the flow velocity of the air passing through the stationary blades increases, the pressure loss between the stationary blades increases. When the flow velocity of the air passing through the stationary blade is very fast (for example, exceeding Mach 1), the air flow is clogged and so-called choke is generated.

  The present invention has been made in view of the above-described problems, and an object of the present invention is to reduce pressure loss in a compressor and suppress generation of choke in a gas turbine engine.

  The present invention adopts the following configuration as means for solving the above-described problems.

  1st invention is a gas turbine engine provided with the compressor which compresses air and sends it to a combustor, Comprising: It is provided in the core flow path in which the stationary blade with which the said compressor is arrange | positioned, The most upstream stationary blade A configuration is adopted in which bleeding means for bleeding the air is further provided upstream of the throat portion between the most upstream stationary vanes.

  According to a second invention, in the first invention, the bleed means opens on the rear stream side with respect to the front edge of the uppermost stream stationary blade and on the upstream side with respect to the throat portion between the uppermost stream stationary blades. The structure of having a bleed port to be used is adopted.

  According to a third aspect, in the first aspect, the bleeder includes a bleed port that is opened upstream of the leading edge of the most upstream stationary blade.

  According to a fourth invention, in the second or third invention, a configuration is adopted in which the extraction port is provided on a tip side of the most upstream stationary blade in the core flow path.

  According to a fifth invention, in any one of the first to fourth inventions, a main nozzle that injects high-temperature gas generated in the combustor, and noise is generated by injecting air into the high-temperature gas injected from the main nozzle. A configuration is adopted in which the microjet nozzle is provided, and the extraction means supplies the extracted air to the microjet nozzle.

According to the present invention, air is extracted by the extraction means on the upstream side of the throat portion of the most upstream stator blade that is the most upstream stator blade.
The throat portion between the most upstream stationary blades, which are the most upstream stationary blades, is the region where the flow path area difference from the upstream side is the largest and the air is most rapidly accelerated. According to the present invention, since a part of the air is extracted upstream from the throat portion, the flow rate in the throat portion is reduced, and thereby the flow velocity of the air passing through the most upstream stationary blade can be reduced. .
For this reason, according to the present invention, the pressure loss in the throat portion can be reduced, and a choke margin (a margin until the choke is generated) can be secured, reducing the pressure loss in the compressor and suppressing the occurrence of the choke. It becomes possible to do.

It is sectional drawing which shows typically schematic structure of the jet engine in 1st Embodiment of this invention. It is a mimetic diagram containing the inlet guide vane with which the jet engine in a 1st embodiment of the present invention is provided. It is a graph which states the effect of the jet engine in 1st Embodiment of this invention. It is sectional drawing which shows typically schematic structure of the jet engine in 2nd Embodiment of this invention. It is a graph which states the effect of the jet engine in 2nd Embodiment of this invention.

  Hereinafter, an embodiment of a gas turbine engine according to the present invention will be described with reference to the drawings. In the following drawings, the scale of each member is appropriately changed in order to make each member a recognizable size. In the following description, a biaxial jet engine will be described as an example of a gas turbine engine.

(First embodiment)
FIG. 1 is a cross-sectional view schematically showing a schematic configuration of the jet engine S1 of the present embodiment. As shown in this figure, the jet engine S1 of this embodiment includes an outer cowl 1, an inner cowl 2, a fan 3, a low pressure compressor 4, a high pressure compressor 5, a combustor 6, and a high pressure turbine 7. A low-pressure turbine 8, a shaft 9, a main nozzle 10, a microjet nozzle 11, and an extraction unit 12.

The outer cowl 1 is a cylindrical member arranged on the most upstream side in the jet engine S1, and an upstream end and a downstream end in the air flow direction are open ends, and the upstream end functions as an air intake port 1a. To do.
As shown in FIG. 1, the outer cowl 1 houses the upstream side of the inner cowl 2 and the fan 3 therein.

The inner cowl 2 is a cylindrical member having a smaller diameter than the outer cowl 1, and the upstream end and the downstream end in the air flow direction are open ends, like the outer cowl 1.
The inner cowl 2 includes a low-pressure compressor 4, a high-pressure compressor 5, a combustor 6, a high-pressure turbine 7, a low-pressure turbine 8, a shaft 9, a main nozzle 10 and the like that are main parts of the jet engine S1. Housed inside.

The inner cowl 2 has a flow path (hereinafter referred to as a core flow path 13) through which a part of the air taken into the outer cowl 1 and high-temperature gas generated by the combustor 6 pass.
As shown in FIG. 1, the outer cowl 1 and the inner cowl 2 are arranged concentrically when viewed from the air flow direction, and are arranged with a gap therebetween. A gap between the outer cowl 1 and the inner cowl 2 serves as a bypass flow path 14 that discharges a remaining portion of the air taken into the outer cowl 1 that does not flow into the core flow path 13 to the outside.
The outer cowl 1 and the inner cowl 2 are attached to the aircraft body by a pylon (not shown).

The fan 3 forms an air flow that flows into the outer cowl 1, and includes a plurality of fan rotor blades 3 a fixed to the shaft 9 and a plurality of fan stationary blades 3 b disposed in the bypass flow path 14. ing.
The shaft 9 described in detail later is divided into two in the radial direction when viewed from the air flow direction. More specifically, the shaft 9 is constituted by a solid first shaft 9a that is a core portion and a hollow second shaft 9b that is disposed outside the first shaft 9a.
The fan rotor blade 3 a is fixed to the first shaft 9 a of the shaft 9.

As shown in FIG. 1, the low-pressure compressor 4 is disposed on the upstream side of the high-pressure compressor 5, and compresses the air sent to the core flow path 13 by the fan 3.
The low-pressure compressor 4 includes a moving blade 4 a fixed to the second shaft 9 b of the shaft 9 and a stationary blade 4 b fixed to the inner wall of the inner cowl 2.
The moving blades 4a are arranged in a ring shape at equal intervals to form one moving blade row. A plurality of stationary blades 4b are also arranged in a ring at regular intervals to form one stationary blade row. In the low-pressure compressor 4, a plurality of stationary blade rows and moving blade rows are alternately arranged starting from the stationary blade row in the air flow direction.
And among the stationary blade row | line | column with which the low pressure compressor 4 is provided, the stationary blade | wing 4b which comprises the stationary blade row | line | column located in the most upstream side is made to be able to rotate centering | focusing on the rotating shaft which faces the radial direction of jet engine S1. And functions as an inlet guide vane 4b1 (uppermost stationary vane) that adjusts the flow direction of the air flowing into the core flow path 13.

As shown in FIG. 1, the high-pressure compressor 5 is disposed on the downstream side of the low-pressure compressor 4, and compresses the air fed from the low-pressure compressor 4 to a higher pressure.
The high-pressure compressor 5 includes a moving blade 5 a that is fixed to the second shaft 9 b of the shaft 9 and a stationary blade 5 b that is fixed to the inner wall of the inner cowl 2.
As with the low-pressure compressor 4, the moving blades 5 a are arranged in a ring shape at equal intervals to constitute one moving blade row. A plurality of stationary blades 5b are also arranged in a ring at regular intervals to constitute one stationary blade row. A plurality of stationary blade rows and moving blade rows are alternately arranged in the air flow direction.

  The combustor 6 is disposed on the downstream side of the high-pressure compressor 5, and burns a mixture of compressed air fed from the high-pressure compressor 5 and fuel supplied from an injector (not shown) to generate high-temperature gas. Is to be generated.

The high-pressure turbine 7 is disposed on the downstream side of the combustor 6 and recovers rotational power from the high-temperature gas discharged from the combustor 6.
The high-pressure turbine 7 includes a plurality of turbine rotor blades 7a fixed to the second shaft 9b of the shaft 9 and a plurality of turbine stationary blades 7b fixed to the core flow path 13. The rectified high temperature gas is received by the turbine rotor blade 7a, and the second shaft 9b is rotationally driven.

The low-pressure turbine 8 is disposed on the downstream side of the high-pressure turbine 7, and further collects rotational power from the high-temperature gas that has passed through the high-pressure turbine 7.
The low-pressure turbine 8 includes a plurality of turbine rotor blades 8a fixed to the first shaft 9a of the shaft 9 and a plurality of turbine stationary blades 8b fixed to the core flow path 13, and the turbine stationary blade 8b The rectified high temperature gas is received by the turbine rotor blade 8a, and the first shaft 9a is rotationally driven.

The shaft 9 is a rod-like member arranged in the air flow direction, and the rotational power recovered by the turbine (the high pressure turbine 7 and the low pressure turbine 8) is converted into the fan 3 and the compressor (the low pressure compressor 4 and the high pressure compression). Machine 5).
As described above, the shaft 9 is divided into two in the radial direction, and is constituted by the first shaft 9a and the second shaft 9b.
The first shaft 9a has the moving blade 4a of the low-pressure compressor 4 and the fan moving blade 3a of the fan 3 attached to the upstream side, and the turbine moving blade 8a of the low-pressure turbine 8 attached to the downstream side.
Further, the second shaft 9b has the moving blade 5a of the high-pressure compressor 5 attached to the upstream side and the turbine moving blade 7a of the high-pressure turbine 7 attached to the downstream side.

The main nozzle 10 is provided further downstream of the low-pressure turbine 8 and injects high-temperature gas that has passed through the low-pressure turbine 8 toward the rear of the jet engine S1.
The thrust of the jet engine S1 is obtained by the reaction when the high temperature gas is injected from the main nozzle 10.

  A plurality of micro jet nozzles 11 are provided around the main nozzle 10 and are intended to reduce noise by blowing air against a jet jet jetted from the main nozzle 10.

  The bleeder 12 is the most upstream stationary vane provided in the compressor (the low pressure compressor 4 and the high pressure compressor 5) that compresses the air and sends it to the combustor 6, and between the inlet guide vanes 4b1 of the low pressure compressor 4 The air that has flowed into the core flow path 13 further upstream than the throat portion S is extracted.

2 is a schematic view showing the periphery of the inlet guide vane 4b1, wherein (a) is a cross-sectional view seen from the same direction as FIG. 1, and (b) is an arrow view seen from the arrow A direction in (a). It is a figure and (c) is an arrow view which looked at only the inlet guide vane 4b1 from the arrow B direction in (a).
As shown in these drawings, the bleeder 12 has a bleed port 12a that is opened downstream from the front edge of the inlet guide vane 4b1 and upstream from the throat S between the inlet guide vanes 4b1. I have.
The bleed port 12a is provided between the inlet guide vanes 4b1, and is provided in an elliptical shape on the tip side (that is, the inner cowl 2) of the inlet guide vane 4b1.

In addition, the extraction unit 12 includes an air flow path 12b that supplies the air flowing in from the extraction port 12a to the micro jet nozzle 11.
The air flow path 12b communicates all the bleed ports 12a and all the micro jet nozzles 11 with each other. However, a plurality of air flow paths that connect only one extraction port 12a and one micro jet nozzle 11 may be provided.

In the jet engine S1 of the present embodiment having such a configuration, in a steady state, air is taken into the outer cowl 1 by driving the fan 3, and a part thereof flows into the core flow path 13.
The air flowing into the core flow path 13 is sequentially compressed by the low pressure compressor 4 and the high pressure compressor 5 and supplied to the combustor 6.
The compressed air supplied to the combustor 6 is mixed with fuel to form an air-fuel mixture. The air-fuel mixture is combusted by the combustor 6 to generate high temperature gas.
The hot gas generated in the combustor 6 passes through the high-pressure turbine 7 and the low-pressure turbine 8 and is injected from the main nozzle 10 to the rear of the jet engine S1. This provides a driving force.

When the high-temperature gas passes through the high-pressure turbine 7, the rotational power is recovered by the high-pressure turbine 7, and the rotor blade 5a of the high-pressure compressor 5 is rotationally driven through the second shaft 9b.
Further, when the high-temperature gas passes through the low-pressure turbine 8, the rotational power is recovered by the low-pressure turbine 8, and the rotor blade 4a of the low-pressure compressor 4 and the fan rotor blade 3a of the fan 3 are rotationally driven through the first shaft 9a. Is done.

And in jet engine S1 of this embodiment, a part of the air which flows through the core flow path 13 is extracted by the extraction part 12 upstream from the throat part S between inlet guide vanes 4b1.
The throat portion S between the inlet guide vanes 4b1 is the region where the flow path area difference from the upstream side is the largest, the air is most rapidly accelerated, and the air is easily clogged. On the other hand, according to the jet engine S1 of the present embodiment, since a part of the air is extracted upstream from the throat portion S, the flow rate in the throat portion S is reduced, and thereby the inlet guide vane 4b1. The flow rate of air passing through the can be reduced.
For this reason, according to the jet engine S1 of the present embodiment, the pressure loss in the throat portion S can be reduced, the choke margin can be secured, the pressure loss in the compressor can be reduced, and the occurrence of choke can be suppressed. it can.

  FIG. 3 is a graph showing the relationship between the Mach number of the inlet guide vane blade surface near the tip and the cord direction distance. As can be seen from this figure, the blade surface Mach number on the suction surface side of the inlet guide vane 4b1 provided in the jet engine S1 of the present embodiment is reduced as compared with the inlet guide vane of the conventional jet engine not provided with the bleed portion 12. Yes.

Further, in the jet engine S1 of the present embodiment, the bleed port 12a of the bleed portion 12 is located on the rear stream side with respect to the front edge of the inlet guide vane 4b1.
For this reason, since the air whose pressure has been slightly increased in the extraction unit 12 can be extracted, air can be extracted easily.
In the jet engine S1 of the present embodiment, air extracted from the micro jet nozzle 11 is supplied. Since the pressurized air is extracted as described above, the extraction unit 12 can supply the extracted air to the microjet nozzle 11 without providing a drive source such as a pump.
That is, in the jet engine S1 of the present embodiment, it is not necessary to provide a separate drive source when injecting air from the micro jet nozzle 11, and air can be easily ejected from the micro jet nozzle 11.

Further, in the jet engine S1 of the present embodiment, the extraction port 12a of the extraction unit 12 is provided on the tip side of the inlet guide vane 4b1, that is, the inner cowl 2.
When the air taken into the outer cowl 1 enters the inner cowl 2, turbulent flow is formed on the inner wall surface of the inner cowl 2, and this turbulent flow is one cause of increased pressure loss.
On the other hand, in the jet engine S1 of the present embodiment, the bleed port 12a is provided for the inner cowl 2 as described above, so that the turbulent flow can be sucked from the bleed port 12a, and the core channel 13 It is possible to further reduce the pressure loss at.

(Second Embodiment)
Next, a second embodiment of the present invention will be described. In the description of the second embodiment, the description of the same parts as in the first embodiment will be omitted or simplified.

4 is a schematic view showing the periphery of the inlet guide vane 4b1, where (a) is a cross-sectional view seen from the same direction as FIG. 1, and (b) is an arrow view seen from the arrow A direction in (a). FIG.
As shown in these drawings, the bleeder 12 includes an annular bleed port 13c that is opened upstream of the front edge of the inlet guide vane 4b1.
The bleed port 12a is provided between the inlet guide vanes 4b1, and is provided on the tip side of the inlet guide vane 4b1 (that is, the inner cowl 2).

  According to the jet engine of this embodiment that employs such a configuration, the pressure of the air to be extracted is lower than that of the first embodiment, but more air can be extracted and the inlet guide can be extracted. The blade surface Mach number in the vane 4b1 can be further reduced.

  FIG. 5 is a graph showing the relationship between the Mach number of the inlet guide vane blade surface near the tip and the cord direction distance. As can be seen from this drawing, the blade surface Mach number on the suction surface side and the pressure surface side of the inlet guide vane 4b1 provided in the jet engine of the present embodiment is higher than that of the inlet guide vane of the conventional jet engine that does not include the bleed portion 12. Reduced.

  As mentioned above, although preferred embodiment of this invention was described referring drawings, this invention is not limited to the said embodiment. Various shapes, combinations, and the like of the constituent members shown in the above-described embodiments are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.

For example, in the above embodiment, an example in which the gas turbine engine of the present invention is applied to a jet engine has been described.
However, the present invention is not limited to this, and can be applied to other gas turbine engines.

Moreover, in the said embodiment, the extraction port with which the extraction part 12 was provided demonstrated the example which is carrying out the ellipse or cyclic | annular shape.
However, the present invention is not limited to this, and the shape of the bleed port can adopt other shapes such as an annular shape, a circle shape, an ellipse shape, a quadrangular shape, and a polygonal shape.

Moreover, in the said embodiment, the structure which supplies the air extracted by the extraction part 12 to the micro jet nozzle 11 was demonstrated.
However, the present invention is not limited to this, and the air extracted by the extraction unit 12 may be used for other purposes or exhausted.

  S1 ... Jet engine (gas turbine engine), 1 ... Outer cowl, 1a ... Air intake port, 2 ... Inner cowl, 3 ... Fan, 3a ... Fan blade, 3b ... Fan stationary blade, 4 ... Low pressure compressor (compressor), 4a ... moving blade, 4b ... static blade, 4b1 ... inlet guide vane (uppermost stationary vane), 5 ... high pressure compressor, 5a ... moving blade, 5b ...... Static blade, 6 ... Combustor, 7 ... High pressure turbine, 7a ... Turbine blade, 7b ... Turbine blade, 8 ... Low pressure turbine, 8a ... Turbine blade, 8b ... Turbine blade , 9 ... Shaft, 9a ... First shaft, 9b ... Second shaft, 10 ... Main nozzle, 11 ... Micro jet nozzle, 12 ... Extraction part (extraction means), 12a ... Extraction port, 12b ... Air channel, 13 ... Core channel, 14 ... By Scan channel, S ...... throat

Claims (5)

A gas turbine engine comprising a compressor that compresses air and feeds it into a combustor,
A bleeder that is provided in a core flow path in which the stationary blades of the compressor are disposed and bleeds the air further upstream than the throat portion between the most upstream stationary blades that are the most upstream stationary blades. equipped with a,
The gas turbine engine according to claim 1, wherein the extraction unit includes an extraction port opened on an inner wall surface of the core flow path . The bleed ports are according to claim 1, wherein a gas, wherein the Ru is opened on the upstream side of the throat portion between and the most upstream vanes between a downstream side of the front edge of the most upstream vanes Turbine engine. The bleed ports are gas turbine engine according to claim 1, wherein the Ru is opened on the upstream side of the front edge of the most upstream vanes.   4. The gas turbine engine according to claim 2, wherein the bleed port is provided on a tip side of the most upstream stationary blade in the core flow path. A main nozzle for injecting high-temperature gas generated in the combustor; and a micro-jet nozzle for injecting air into the high-temperature gas injected from the main nozzle to reduce noise.
The gas turbine engine according to any one of claims 1 to 4, wherein the extraction unit supplies the extracted air to the micro jet nozzle.

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