KR20110125717A - Mixed-flow type compressor - Google Patents

Mixed-flow type compressor Download PDF

Info

Publication number
KR20110125717A
KR20110125717A KR1020100045222A KR20100045222A KR20110125717A KR 20110125717 A KR20110125717 A KR 20110125717A KR 1020100045222 A KR1020100045222 A KR 1020100045222A KR 20100045222 A KR20100045222 A KR 20100045222A KR 20110125717 A KR20110125717 A KR 20110125717A
Authority
KR
South Korea
Prior art keywords
flow
compressor
impeller
axial
diffuser
Prior art date
Application number
KR1020100045222A
Other languages
Korean (ko)
Inventor
민성기
김유일
최재호
Original Assignee
국방과학연구소
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 국방과학연구소 filed Critical 국방과학연구소
Priority to KR1020100045222A priority Critical patent/KR20110125717A/en
Publication of KR20110125717A publication Critical patent/KR20110125717A/en

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D23/00—Other rotary non-positive-displacement pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2210/00—Working fluids
    • F05D2210/10—Kind or type
    • F05D2210/12—Kind or type gaseous, i.e. compressible
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S417/00—Pumps

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

PURPOSE: A diagonal flow type compressor is provided to reduce the outer circumference of a compressor comparing to a centrifugal compressor. CONSTITUTION: A diagonal flow type compressor comprises a diagonal flow type impeller(10) and multiple diffuser vanes(20). The diagonal flow type impeller has an inlet part and an outlet part facing to a diagonal radial direction. Multiple diffuser vanes are curve type. The outlet part of the diagonal flow type impeller and the inlet part of the diffuser vane have the same angle as to the diagonal flow type flow path shape. The axial type outlet of the diffuser vane has a tip-end part. The tip-end part is perpendicularly opened on the flow path.

Description

사류형 압축기{MIXED-FLOW TYPE COMPRESSOR}Four-flow compressor {MIXED-FLOW TYPE COMPRESSOR}

본 발명은 사류형 압축기에 관한 것으로서, 더욱 상세하게는 초소형 터보제트엔진에 적용되며, 전진익형을 갖는 사류형 임펠러와 사류형 입구부 및 축류형 출구부를 갖는 복수 개의 디퓨저 베인으로 구성된 사류형 압축기에 관한 것이다.BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a quadrature compressor, and more particularly, to a miniature turbojet engine, in which a quadruple compressor including a quadruple impeller having a forward wing type and a plurality of diffuser vanes having a quadruple inlet and an axial outlet is provided. It is about.

일반적으로 항공기의 한정된 공간내에 항공용 터빈엔진을 장착시키기 위해서는 가능한 한 터빈엔진의 부피와 무게를 줄일 수 있는 설계가 필요하며, 특히 최근에는 터빈 엔진의 부피를 좌우하는 전단면적은 항공기 항력과 직접적인 관련이 있어 이를 최소화하기 위한 연구가 계속되어 왔다.In general, in order to mount an aviation turbine engine within a limited space of an aircraft, it is necessary to design a design that reduces the volume and weight of the turbine engine as much as possible. There has been research to minimize this.

항공용 터빈엔진 중 가스터빈엔진은 발전기, 압축기, 연소기, 터빈, 배기노즐로 구성되어 있다. 이중 압축기는 일반적으로 흡입공기의 전압력을 상승시키는 임펠러와, 임펠러에서 압력이 상승된 공기의 속도를 줄여 연소기에서 연소특성을 향상시켜 주는 디퓨저와, 디퓨져 출구 유동방향을 축방향으로 바꿔주며 연소기의 연소특징을 향상시켜 주는 디스월러로 구성되며, 또한 압축기의 전단면적의 크기가 가스터빈엔진의 전단면적의 크기에 결정적인 영향을 미친다.The gas turbine engine of aviation turbine engine is composed of generator, compressor, combustor, turbine and exhaust nozzle. Dual compressors generally have an impeller that increases the total pressure of the intake air, a diffuser that improves combustion characteristics in the combustor by reducing the velocity of the air with increased pressure in the impeller, and changes the flow direction of the diffuser outlet in the axial direction and burns the combustor. It consists of a deswaler to improve the characteristics, and the shear area of the compressor has a decisive influence on the size of the shear area of the gas turbine engine.

또한, 가스터빈엔진에 사용되는 압축기는 주로, 원심형 압축기, 축류형 압축기, 사류형 압축기가 있으며, 이중 원심형 압축기는 단당 압축비가 높고 제작비용이 낮으나 전단면적이 크다는 문제점이 있다. 또한, 축류형 압축기는 전단면적은 작으나 단당 압축비가 낮고 제작비용이 높다는 문제점이 있다. In addition, the compressor used in the gas turbine engine mainly includes a centrifugal compressor, an axial compressor, and a four-flow compressor. The double centrifugal compressor has a high compression ratio per unit, a low manufacturing cost, but a large shear area. In addition, the axial compressor has a problem that the shear area is small but the compression ratio per unit and the manufacturing cost is high.

이러한 양 압축기의 단점을 보완하기 위한 것이 사류형 압축기이다. 그러나 종래의 사류형 압축기는 단당 압축비가 원심압축기와 거의 동일하고, 전단면적은 축류형 압축기와 원심형 압축기의 중간 정도의 크기이나 효율이 낮다는 문제점이 있었다.To compensate for the shortcomings of both compressors, the four-flow compressor. However, the conventional four-flow compressor has a problem that the compression ratio per unit is almost the same as that of the centrifugal compressor, and that the shear area is about the same size or efficiency as that of the axial compressor and the centrifugal compressor.

그러므로, 종래의 사류형 압축기를 더욱 개선하여 단당 압축비가 높고, 전단면적은 작으며, 구성이 간단하면서도 효율이 높은 형상으로 이루어진 임펠러 및 디퓨져 베인을 갖는 사류형 압축기가 요구되어 왔다.Therefore, there has been a demand for a four-flow compressor having impeller and diffuser vanes having a high compression ratio per unit, a small shear area, a simple configuration, and a high efficiency by further improving the conventional four-flow compressor.

본 발명은 상기한 종래의 문제점을 해결하기 위해 안출된 것으로, 임펠러의 효율 및 압축비를 높이고 더 작은 직경내에서 효과적으로 임펠러에서의 높은 동압을 정압으로 전환시킬 수 있도록 전진익형의 사류형 임펠러와 사류형 입구부 및 축류형 출구부를 갖는 복수 개의 디퓨져 베인을 포함하는 사류형 압축기를 제공하는 것을 목적으로 한다.SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned conventional problems. The present invention is directed to a quadruple type impeller and quadrature type so as to increase the efficiency and compression ratio of the impeller and to effectively convert the high dynamic pressure in the impeller into the static pressure within a smaller diameter. It is an object to provide a four-flow compressor comprising a plurality of diffuser vanes having an inlet and an axial outlet.

상기의 목적을 달성하기 위해 본 발명은, 초소형 터보제트엔진용 사류형 압축기로서, 전진익형의 입구부와 축방향에서 대각선 반경방향으로 향하는 출구부를 갖는 사류형 임펠러와, 사류형 입구부 및 초소형 터보제트엔진의 축 방향과 나란한 축류형 출구부를 갖는 곡선형상인 복수 개의 디퓨져 베인을 포함하는 것을 특징으로 한다.SUMMARY OF THE INVENTION In order to achieve the above object, the present invention relates to a quadruple compressor for a micro turbojet engine, comprising a four-flow impeller having an inlet portion of the forward blade type and an outlet portion that faces in the radial direction diagonally in the axial direction, and the four-flow inlet portion and the micro turbo. And a plurality of curved diffuser vanes having an axial outlet portion parallel to the axial direction of the jet engine.

또한, 상기 사류형 임펠러의 출구부와 상기 디퓨져 베인의 사류형 입구부는 사류형 유로형상에 있어서 서로 동일한 각도를 갖는 것을 특징으로 한다.In addition, the outlet portion of the cross-flow impeller and the cross-flow inlet of the diffuser vane are characterized by having the same angle to each other in the shape of the cross-flow channel.

또한, 상기 디퓨져 베인의 출구부는 유로에 수직으로 개구된 선단부를 갖는 것을 특징으로 한다.In addition, the outlet portion of the diffuser vane is characterized in that it has a front end that is perpendicular to the flow path.

본 발명에 의한 사류형 압축기에 의하면, 전진익형의 사류형 임펠러로 인해 원심형 압축기와 동일한 압력비를 내면서도 원심형 압축기에 비해 압축기의 외경을 현저히 감소시킬 수 있다. According to the four-flow compressor according to the present invention, the outer diameter of the compressor can be remarkably reduced compared to the centrifugal compressor due to the forward wing type four-flow impeller.

또한, 사류형 입구부와 축류형 출구부를 갖는 디퓨져 베인은 원심형 압축기에서의 반경형 디퓨져와 축류형 디스월러의 역할을 함께 수행하므로, 원심형 압축기의 직경보다 작은 직경으로 임펠러서에서 형성된 높은 동압을 정압으로 전환 시킬 수 있다.In addition, the diffuser vanes having a cross-flow inlet and an axial flow-out part serve as a radial diffuser and an axial flow distributor in a centrifugal compressor, so that the high dynamic pressure formed in the impeller with a diameter smaller than that of the centrifugal compressor Can be converted to static pressure.

또한, 디퓨져 베인의 사류형 입구부는 사류형으로 형성되어 있어 사류형 임펠러의 유동이 원활하게 디퓨져 베인내로 유입될 수 있다.In addition, the cross-flow inlet portion of the diffuser vane is formed in a cross-flow shape, the flow of the cross-flow impeller can be smoothly introduced into the diffuser vane.

또한, 디퓨져 베인의 축류형 출구부로 인해 연소기로의 공기유입이 원활하게 이루어질 수 있다.In addition, due to the axial outlet portion of the diffuser vanes, the inflow to the combustor can be made smoothly.

도 1은 초소형 터보제트엔진의 대략적 구성도이다.
도 2는 초소형 터보제트엔진에서 본 발명에 의한 사류형 압축기를 나타내는 단면도이다.
도 3은 본 발명에서의 사류형 임펠러 및 디퓨져 베인을 나타내는 자오면이다.1 is a schematic diagram of a micro turbojet engine.
2 is a cross-sectional view showing a four-flow compressor according to the present invention in a micro turbojet engine.
Figure 3 is a meridional plane showing the cross-flow impeller and diffuser vanes in the present invention.

이하 본 발명에 의한 사류형 압축기의 바람직한 실시예를 첨부된 도면을 참고하여 설명한다.Hereinafter, a preferred embodiment of the four-flow compressor according to the present invention will be described with reference to the accompanying drawings.

도 1은 초소형 터보제트엔진의 대략적 구성도이며, 도 2는 초소형 터보제트엔진에서 본 발명에 의한 사류형 압축기를 나타내는 단면도이고, 도 3은 본 발명에서의 사류형 임펠러 및 디퓨져 베인을 나타내는 자오면이다.1 is a schematic configuration diagram of an ultra-small turbojet engine, and FIG. 2 is a cross-sectional view showing a four-flow compressor according to the present invention in an ultra-small turbojet engine, and FIG. 3 is a meridian showing the four-flow impeller and diffuser vanes in the present invention. .

도 1에 도시된 바와 같이 초소형 터보제트엔진은 발전기(A), 압축기(B), 연소기(C), 터빈(D) 및 배기노즐(E)을 포함하여 이루어지며, 본 발명에서의 압축기(B)는 축류형 터빈에 의해서 구동된다.As shown in FIG. 1, the micro turbojet engine includes a generator A, a compressor B, a combustor C, a turbine D, and an exhaust nozzle E, and the compressor B of the present invention. Is driven by an axial turbine.

본 발명은 도 2에 도시된 바와 같이, 압축기(B)에 관련된 것으로, 상기 압축기(B)는 흡입구(30), 사류형 임펠러(10), 디퓨져 베인(20)을 포함하는 사류형 압축기이다.The present invention relates to a compressor (B), as shown in FIG. 2, which is a four-flow compressor including a suction port (30), a four-flow impeller (10), and a diffuser vane (20).

상기 흡입구(30)는 내부에 발전기 등을 수용하고 복수 개의 스트러트로 지지되며, 공력(空力)면에서는 엔진 입구부로 들어오는 공기를 원활하게 사류형 임펠러(10)로 유입될 수 있도록 한다.The intake port 30 accommodates a generator and the like therein and is supported by a plurality of struts, and allows the air flowing into the engine inlet to smoothly flow into the crossflow impeller 10 in the aerodynamic surface.

또한, 상기 사류형 임펠러(10)는 상기 흡입구(30) 후방에 위치하며, 그 입구부는 도 3에 도시된 바와 같이, 팁(11)이 허브(12)보다 앞서는 형상인 전진익형의 임펠러 형태로 이루어져 있으며, 그 출구부는 축방향에서 대각선 반경방향으로 향하는 형상으로 이루어져 있다. 이러한 형상으로 인해 천음속 영역에서 압력손실을 최소화할 수 있다. 또한, 본 발명에서의 사류형 임펠러(10)는 긴 임펠러 날개와 그사이에 상대적으로 짧은 임펠러 날개를 갖는 구성으로 이루어져 있다.In addition, the four-flow impeller 10 is located behind the suction port 30, the inlet portion thereof, as shown in Figure 3, the tip 11 in the form of a forward wing-type impeller shape ahead of the hub 12 The outlet portion has a shape facing in the radial direction diagonally from the axial direction. This shape minimizes pressure loss in the transonic region. In addition, the crossflow impeller 10 in this invention consists of a structure which has a long impeller wing and a relatively short impeller wing between them.

상기 디퓨져 베인(20)은 사류형 입구부(21)와 초소형 터보제트엔진의 축 방향과 나란한 축류형 출구부(22)로 형성되어 있으며, 상기 사류형 입구부(21)는 사류형 유로형상에 있어서 상기 사류형 임펠러(10)의 출구부와 동일한 각도를 갖도록 형성되며, 이로 인해 상기 사류형 임펠러(10)를 통과한 공기유동이 원활히 상기 디퓨져 베인(20) 내로 유입될 수 있다.The diffuser vane 20 is formed of a vortex flow inlet 21 and an axial flow outlet 22 parallel to the axial direction of the ultra-small turbojet engine. In this case, it is formed to have the same angle as the outlet of the crossflow impeller 10, and thus air flow passing through the crossflow impeller 10 may be smoothly introduced into the diffuser vane 20.

또한, 상기 디퓨져 베인의 축류형 출구부(22)는 선단부가 유로에 수직하게 형성되고, 초소형 터보제트엔진의 축 방향과 나란한 방향으로 개구되어 연소기(40)를 향하는 공기유동이 잘 이어질 수 있도록 구성되어 있다. 즉, 상기 디퓨져 베인(20)은 그 내부유동이 사류형으로 유입되어 축류형으로 유출되는 곡선형으로 이루어져 있다. 이러한 형상의 디퓨져 베인(20)은 원심압축기의 반경형 디퓨져와 축류형 디스월러의 역활을 동시에 할 수 있다.
In addition, the axial flow outlet portion 22 of the diffuser vane is formed so that the tip portion is formed perpendicular to the flow path, and is opened in a direction parallel to the axial direction of the ultra-small turbojet engine so that the air flow toward the combustor 40 can be continued. It is. That is, the diffuser vane 20 has a curved shape in which the internal flow flows into the crossflow and flows out into the axial flow. The diffuser vane 20 of this shape can simultaneously serve as a radial diffuser of the centrifugal compressor and an axial flow dispenser.

다음으로, 초소형 터보제트엔진의 내부로 들어온 공기의 흐름에 대하여 설명한다. Next, a description will be given of the air flow into the micro turbojet engine.

상기 초소형 터보제트엔진의 내부로 들어온 공기유동은 흡입구(30)를 지나, 전진익형의 사류형 임펠러(10)로 유입되고, 상기 사류형 임펠러(10)에서 공기유동의 정압력과 동압력이 함께 높아지며, 상기 사류형 임펠러(10)를 통과한 후 사류형 임펠러(10)의 출구부와 동일한 각도로 연결되는 디퓨져 베인의 입구부(21)로 유입되고, 이후 디퓨져 베인의 축류형 출구부(22)를 통하여 배출되어 연소기(40)로 유입된다. The air flow introduced into the inside of the micro turbojet engine passes through the suction port 30 and enters the forward wing type impeller 10, and the positive pressure and the dynamic pressure of the air flow increase in the airflow impeller 10 together. After passing through the crossflow impeller (10), the inlet portion (21) of the diffuser vanes connected at the same angle as the outlet of the crossflow impeller (10) is introduced, and then the axial flow outlet portion (22) of the diffuser vanes. It is discharged through and enters the combustor 40.

이때, 상기 디퓨져 베인(20)의 내부에서는 동압력이 정압력으로 대부분 전환되어 디퓨져 베인의 축류형 출구부(22)에서의 공기유동속도는 충분히 낮아지고, 정압력은 더욱 증가하게 된다. 이후 공기유동은 분무된 연료와 함께 혼합가스 상태에서 연소과정을 거친 후 터빈으로 유입되어 팽창과정을 거치면서 압축기(B)와 발전기(A)를 구동시킬 수 있는 회전력을 얻게 되고, 배기노즐(E)을 지나면서 추력을 낼 수 있는 높은 속도에너지로 전환된다.
At this time, the inside of the diffuser vane 20, the dynamic pressure is mostly converted to the positive pressure, the air flow rate at the axial outlet 22 of the diffuser vane is sufficiently low, the positive pressure is further increased. After that, the air flow is injected into the turbine after the combustion process in the mixed gas state with the atomized fuel, and is then expanded to obtain a rotational force capable of driving the compressor (B) and the generator (A), and the exhaust nozzle (E). ) Is converted into high velocity energy that can generate thrust.

이상에서는 본 발명의 바람직한 실시예를 설명하였으나, 본 발명은 이에 한정되는 것은 아니며, 해당분야의 통상의 지식을 가진자라면 본 발명의 청구범위에 기재된 본 발명의 기술적 사상을 벗어나지 않는 범위내에서 다양한 변경이 가능할 것이다.In the above description of the preferred embodiment of the present invention, the present invention is not limited thereto, and a person of ordinary skill in the art may have various modifications without departing from the technical spirit of the present invention described in the claims of the present invention. Changes will be possible.

A:초소형 터보제트엔진의 발전기 B: 초소형 터보제트엔진의 압축기
C:초소형 터보제트엔진의 연소기 D:초소형 터보제트엔진의 터빈
E:초소형 터보제트엔진의 배기노즐
10: 사류형 임펠러 11: 팁 12: 허브 20: 디퓨져 베인
21: 디퓨져 베인의 사류형 입구부 22: 디퓨져 베인의 축류형 출구부
30: 흡입구 40: 연소기A: Generator of ultra-small turbojet engine B: Compressor of ultra-small turbojet engine
C: Combustor of ultra-small turbojet engine D: Turbine of ultra-small turbojet engine
E: Exhaust nozzle for ultra-small turbojet engine
10: Quadrature impeller 11: Tip 12: Hub 20: Diffuser vanes
21: Convection inlet of diffuser vane 22: Axial outlet of diffuser vane
30: inlet 40: combustor

Claims (3)

초소형 터보제트엔진용 사류형 압축기로서,
전진익형의 입구부와 축방향에서 대각선 반경방향으로 향하는 출구부를 갖는 사류형 임펠러(10)와,
사류형 입구부(21) 및 초소형 터보제트엔진의 축 방향과 나란한 축류형 출구부(22)를 갖는 곡선형상인 복수 개의 디퓨져 베인(20)를 포함하는 것을 특징으로 하는 사류형 압축기.A quadrature compressor for an ultra-small turbojet engine,
A crossflow type impeller 10 having an inlet portion of the forward blade type and an outlet portion that faces in the radial direction diagonally in the axial direction,
A four-flow compressor comprising a plurality of curved diffuser vanes (20) having a four-flow inlet (21) and an axial outlet (22) parallel to the axial direction of the ultra-small turbojet engine. 제1항에 있어서,
상기 사류형 임펠러(10)의 출구부와 상기 디퓨져 베인의 사류형 입구부(21)는 사류형 유로형상에 있어서 서로 동일한 각도를 갖는 것을 특징으로 하는 사류형 압축기.The method of claim 1,
A four-flow compressor, characterized in that the outlet portion of the cross-flow impeller (10) and the cross-flow inlet portion (21) of the diffuser vanes have the same angle to each other in the cross-flow flow path shape. 제1항에 있어서,
상기 디퓨져 베인의 축류형 출구부(22)는 유로에 수직으로 개구된 선단부를 갖는 것을 특징으로 하는 사류형 압축기.The method of claim 1,
And the axial outlet portion (22) of the diffuser vane has a tip portion opened perpendicular to the flow path.
KR1020100045222A 2010-05-14 2010-05-14 Mixed-flow type compressor KR20110125717A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020100045222A KR20110125717A (en) 2010-05-14 2010-05-14 Mixed-flow type compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020100045222A KR20110125717A (en) 2010-05-14 2010-05-14 Mixed-flow type compressor

Publications (1)

Publication Number Publication Date
KR20110125717A true KR20110125717A (en) 2011-11-22

Family

ID=45395052

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020100045222A KR20110125717A (en) 2010-05-14 2010-05-14 Mixed-flow type compressor

Country Status (1)

Country Link
KR (1) KR20110125717A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106989032A (en) * 2017-03-13 2017-07-28 南京航空航天大学 A kind of Novel inclined is wandered about as a refugee heart combined compressor
US11022142B2 (en) 2018-01-24 2021-06-01 Hanwha Aerospace Co., Ltd. Diffuser for compressor
CN113982988A (en) * 2020-04-16 2022-01-28 李伟 Centrifugal axial flow turbine and novel jet engine mode and operation method

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106989032A (en) * 2017-03-13 2017-07-28 南京航空航天大学 A kind of Novel inclined is wandered about as a refugee heart combined compressor
CN106989032B (en) * 2017-03-13 2022-12-06 南京航空航天大学 Oblique flow-centrifugal combined compressor
US11022142B2 (en) 2018-01-24 2021-06-01 Hanwha Aerospace Co., Ltd. Diffuser for compressor
CN113982988A (en) * 2020-04-16 2022-01-28 李伟 Centrifugal axial flow turbine and novel jet engine mode and operation method
CN113982988B (en) * 2020-04-16 2023-04-25 李伟 Centrifugal axial flow turbine and novel jet engine mode and operation method

Similar Documents

Publication Publication Date Title
US3540682A (en) Turbofan type engine frame and support system
US8186962B2 (en) Fan rotating blade for turbofan engine
EP2098714B1 (en) High bypass-ratio turbofan jet engine
US10359051B2 (en) Impeller shroud supports having mid-impeller bleed flow passages and gas turbine engines including the same
US9033668B2 (en) Impeller
US20130084174A1 (en) Strut rods for structural guide vanes
US10267214B2 (en) Compressor inlet recirculation system for a turbocharger
US11131205B2 (en) Inter-turbine ducts with flow control mechanisms
EP3708804A1 (en) Impeller tip cavity
US10519976B2 (en) Fluid diodes with ridges to control boundary layer in axial compressor stator vane
CA2964988C (en) Assembly and method for influencing flow through a fan of a gas turbine engine
CN108506111A (en) A kind of microminiature fanjet
KR20110125717A (en) Mixed-flow type compressor
JP6651404B2 (en) Turbo machinery
CA2938121C (en) Counter-rotating compressor
US10876549B2 (en) Tandem stators with flow recirculation conduit
JP4143901B2 (en) Turbofan engine
CN114738115A (en) Gas turbine engine with contra-rotating centrifugal compressor driven by contra-rotating centripetal turbine
CN113279857B (en) High thrust-weight ratio gas turbine generator suitable for unmanned aerial vehicle
KR20110083363A (en) Impeller and compressor
CN108612597B (en) Fan layout structure for aircraft engine
CN105240159A (en) Jet engine
CN116988890A (en) Single rotor turbofan engine
JP2020051307A (en) Axial flow compressor

Legal Events

Date Code Title Description
A201 Request for examination
E601 Decision to refuse application