公开(公告)号：US06250068B1

公开(公告)日：2001-06-26

申请号：US09356317

申请日：1999-07-16

Applicant: Katsuhiko Tajima ,  Katsutoshi Higuma ,  Akitaka Tateishi

Inventor： Katsuhiko Tajima ,  Katsutoshi Higuma ,  Akitaka Tateishi

IPC: F02G100

CPC classification number: F02C7/052 ,  F01D25/02 ,  F02C7/047 ,  F02C7/05

Abstract: According to the present invention, the shape of a passage in an intake-air duct communicated with the suction side of the intake-air filter is regulated so that snow is heaped up in the intake-air duct, and accordingly, the volume of snow reaching the intake-air filter is reduce in order to prevent the intake-air filter from clogging, and to prevent the flow rate of intake-air into a gas turbine from being lowered. In order to attain the above-mentioned purpose, there is provided, according to the present invention, an air-intake method for a gas turbine, in which intake-air 18 taken from a fresh air intake port is fed downward through a second intake-air duct in a substantially vertical direction, and then is fed in a substantially horizontal direction. Thereafter, dust is removed from the intake-air within an intake-air filter chamber, and then, is led into the gas turbine.

Abstract translation: 根据本发明，与进气滤清器的吸入侧连通的进气管道中的通道的形状被调节，使得在进气管道中堆积积雪，因此，积雪量 为了防止吸入空气过滤器堵塞，并且防止进入燃气轮机的进气流量降低，达到进气过滤器的速度降低。 为了实现上述目的，根据本发明，提供了一种用于燃气轮机的进气方法，其中从新鲜空气吸入口取入的进气18通过第二进气口向下供给 在大致垂直方向上的空气管道，然后沿基本上水平的方向进给。 此后，在进气空气过滤室内从吸入空气除去灰尘，然后被引入燃气轮机。

公开(公告)号：US5694763A

公开(公告)日：1997-12-09

申请号：US507686

申请日：1990-04-11

Applicant: Armand F. Amelio ,  Richard S. Barnard ,  James J. Manzolli

Inventor： Armand F. Amelio ,  Richard S. Barnard ,  James J. Manzolli

IPC: B64D33/02 ,  F02C7/042 ,  F02C7/047 ,  F02C7/05 ,  F02C7/055

CPC classification number: F02C7/05 ,  B64D33/02 ,  F02C7/042 ,  F02C7/047 ,  B64D2033/0286 ,  Y02T50/671 ,  Y10T137/0645

Abstract: A turbine engine inlet system includes a curved duct 14 to deliver air to the engine, an inlet lip 16 to smooth the entry of air flowing into the duct, a forward inlet section 18 submerged within the aircraft skin contour to provide a degree of ram recovery to the duct, and a movable air deflector 20 which is flush with the forward inlet section 18 during normal flight conditions and extended to slightly above the inlet lip 16 during icing conditions.

Abstract translation: 涡轮发动机入口系统包括用于将空气输送到发动机的弯曲管道14，用于平滑流入管道的空气进入的入口唇缘16，浸没在飞机皮肤轮廓内的前进入部分18，以提供一定程度的柱塞恢复 以及可移动的空气导流板20，其在正常飞行条件期间与前进入部分18齐平并且在结冰条件期间延伸到略高于入口唇缘16的上方。

公开(公告)号：US4713934A

公开(公告)日：1987-12-22

申请号：US438636

申请日：1982-11-02

Applicant: Terence R. Pellow

Inventor： Terence R. Pellow

IPC: F02C7/05 ,  F02G3/00

CPC classification number: F02C7/05 ,  B64D33/02 ,  B64D2033/022 ,  B64D2033/0293

Abstract: An air intake for a gas turbine engine compressor comprises an arcuate primary duct which is in communication with the compressor of the gas turbine engine and which is provided with frangible wall portion. The frangible wall portion provides a barrier between the primary duct and a secondary duct and is so positioned and adapted as to be impacted and penetrated by a foreign body, such as a bird, which is above a predetermined weight and which has been ingested through the inlet of the primary duct. After penetrating the wall portion the foreign body passes through the secondary duct and is discharged therefrom at a location remote from the primary duct.

Abstract translation: 用于燃气涡轮发动机压缩机的进气口包括与燃气涡轮发动机的压缩机连通并且设置有易碎壁部分的弓形主管道。 易碎壁部分在主管道和次管道之间提供阻挡物，并且被定位并适于被诸如鸟类的异物撞击并穿透，异物超过预定重量并且已经通过 主管道入口。 在穿透壁部分之后，异物通过次级管道并从远离主管道的位置排出。

公开(公告)号：US4712980A

公开(公告)日：1987-12-15

申请号：US860864

申请日：1986-05-08

Applicant: Jean-Marie L. Gely ,  Marius J. Goutines ,  Geordes Meauze

Inventor： Jean-Marie L. Gely ,  Marius J. Goutines ,  Geordes Meauze

IPC: F01D5/14 ,  F02C7/04 ,  F02C7/05 ,  F01D5/16

CPC classification number: F01D5/147 ,  F01D5/20 ,  F02C7/05 ,  Y02T50/671 ,  Y02T50/673 ,  Y10S415/914

Abstract: A fairing formed from a dihedron of which the faces, disposed in the extension of the intrados and extrados surfaces follow the aerodynamic profile of the blade. Such rejoin the blade at a small radius portion constituting a leading edge. The fairing imparts a characteristic enabling the optimum efficiency of the fan to be approached. The useful height of the dihedron is at least 5% of the height of the blade.

Abstract translation: 由二面体形成的整流罩，其设置在内部和外部表面的延伸部中的面遵循叶片的空气动力学轮廓。 这样，在构成前缘的小半径部分上重新加入刀片。 整流罩具有使风扇达到最佳效率的特点。 二面体的有用高度是叶片高度的至少5％。

公开(公告)号：US4346860A

公开(公告)日：1982-08-31

申请号：US213453

申请日：1980-12-05

Applicant: Donald J. Tedstone

Inventor： Donald J. Tedstone

IPC: B64D33/02 ,  F02C7/05 ,  F02G3/00

CPC classification number: B64D33/02 ,  F02C7/05

Abstract: A permanently fixed fairing is provided extending across the air duct coinciding with the opening in the air duct to the air intake of a gas turbine engine. The fairing is in the form of an airfoil vane with a high pressure concave surface and a low pressure convex surface extending between the leading edge and trailing edge of the fairing and shaped such that the leading edge portion of the fairing is in the direction of the longitudinal axis of the air duct while the trailing edge portion of the fairing is in the direction of the air intake of the engine such that the fairing will divert air into the intake. A deflecting flap is hinged to the wall of the duct in a first position for a non-icing mode whereby the flap is clear of the air duct and in a second position whereby the trailing edge of the flap is adjacent the leading edge of the fairing during an icing mode.

Abstract translation: 提供了永久固定的整流罩，其横跨空气管道延伸，与空气管道中与燃气涡轮发动机的进气口的开口重合。 整流罩是具有高压凹面的翼型叶片和在整流罩的前缘和后缘之间延伸的低压凸面，使得整流罩的前缘部分沿着整流罩的方向 整流罩的后缘部分处于发动机进气方向上，从而整流罩将空气转入进气口。 在非结冰模式的第一位置中，偏转翼片被铰接到管道的壁上，由此翼片远离空气管道并且处于第二位置，由此翼片的后缘邻近整流罩的前缘 在结冰模式下。

公开(公告)号：US4070827A

公开(公告)日：1978-01-31

申请号：US682195

申请日：1976-05-03

Applicant: Charles R. Vanfleet ,  William C. Ruehr

Inventor： Charles R. Vanfleet ,  William C. Ruehr

IPC: B64D33/02 ,  F02C7/05 ,  F02C7/04

CPC classification number: F02C7/05

Abstract: A method and apparatus are disclosed for limiting ingestion of debris into the inlet of a gas turbine engine. The invention includes providing first means in communication with a source of fluid under pressure for introducing at least one jet of fluid at a point aft of the leading edge of a nacelle associated with the engine inlet. The first means are adapted to discharge the fluid jet away from the leading edge and in the aft direction to establish a low pressure region aft of the leading edge and in sufficient proximity to a second vortex formation region so as to draw airflows from the second region into the low pressure region and away from the engine inlet.

Abstract translation: 公开了一种用于限制将碎屑摄取到燃气涡轮发动机的入口中的方法和装置。 本发明包括提供与在压力下的流体源连通的第一装置，用于在与发动机入口相关联的机舱的前边缘的后部点处引入至少一个流体射流。 第一装置适于将流体射流从前缘和后方排出，以建立前缘的后部的低压区域并且足够靠近第二涡流形成区域，以便从第二区域抽出气流 进入低压区域并远离发动机入口。

公开(公告)号：US3952972A

公开(公告)日：1976-04-27

申请号：US536155

申请日：1974-12-24

Applicant: Donald Tedstone ,  Hans-Herman Schaum ,  John James Sanderson

Inventor： Donald Tedstone ,  Hans-Herman Schaum ,  John James Sanderson

IPC: B64D33/02 ,  F02C7/05

CPC classification number: B64D33/02 ,  F02C7/05 ,  B64D2033/0246 ,  B64D2033/0293

Abstract: The invention relates to an improvement to an installation for preventing the ingress of super-cooled water, ice, snow and other debris as taught in U.S. Pat. No. 3,329,377. In the patent, an inertial separator effect is used to prevent ingress of super cooled water, ice, snow and other debris to an aircraft engine. The effect is obtained by an installation including a duct formed in a sub-nacelle of the engine to extend generally longitudinally of the engine. An air deflecting surface in the duct confines the incoming air to a passage of reduced cross section, and an opening in the duct wall downstream of the deflecting surface is formed between the trailing edge of the deflecting surface and the leading edge of a rearward portion of the duct, the opening in the duct wall communicating with the engine air intake. In accordance with the present invention, any or all of the following improvements are made to the above installation:A. a cyclic ice shedder is provided to extend inwardly from the leading edge of the rearward portion;B. the rearward portion is formed in the shape of a hopper which is spaced from the outlet passage;C. a fairing is provided at the trailing edge of the deflecting surface; andD. a lower surface of the duct is contoured between the trailing edge of the deflecting surface and the discharge opening of the duct to provide a fairing between the cross sectional area of the duct at the trailing edge of the deflecting surface and the cross sectional area at the discharge opening.

Abstract translation: 本发明涉及一种用于防止过冷却水，冰，雪和其它碎屑进入的装置的改进，如美国专利No. 第3,329,377号。 在该专利中，使用惯性分离器效应来防止超级冷却水，冰，雪和其他碎屑进入飞机发动机。 该效果通过包括形成在发动机的子舱中的管道的装置获得，其大致沿发动机纵向延伸。 管道中的空气偏转表面将进入的空气限制在横截面减小的通道中，并且偏转表面下游的管道壁中的开口形成在偏转表面的后缘和后退部分的前边缘之间 管道，管道壁中的开口与发动机进气口连通。 根据本发明，对上述安装进行以下任何或全部改进：

公开(公告)号：US3702121A

公开(公告)日：1972-11-07

申请号：US3702121D

申请日：1971-01-20

Applicant: ROHR INDUSTRIES INC

Inventor： MILLMAN VICTOR

IPC: F02C7/04 ,  F02C7/05 ,  F02B27/00

CPC classification number: F02C7/04 ,  F02C7/05 ,  Y10T137/0536

Abstract: IN SUBSTANTIALLY THE SAME WAY TO IMPROVE THE RECOVERY OF THE INLET. THE FENCE MAY BE FIXEDLY MOUNTED IN ACTIVE POSITION OR MAY BE RETRACTABLE WITHIN OR FLUSH UPON THE FORWARD PORTION OF THE HOUSING.

SYSTEM INCLUDES A HOUSING WHICH COMPRISES ALL OR PART ON AN INLET THROAT FOR DIRECTING FLOW OF INTAKE AIR FROM AMBIENT ATMOSPHERE TO COMPRESSOR OF JET ENGINE, HOUSING HAS THIN, SLIGHTLY ROUNDED INLET LIP. AT STANDSTILL OR LOW GROUND ROLL SPEEDS, COMPRESSOR DEMAND PULLS AIR IN LATERALLY ACROSS INLET LIP AMD THIS AIR BREAKS AWAY FROM HOUSING INNER WALL AT SMALL CURVATURE OF LIP, DISTURBING TOTAL FLOW AND OFTEN CAUSING COMPRESSOR STALL AND ENGINE FLAMEOUT. PERFORATE FENCE, WHICH IS PREFERABLY WIRE SCREEN, EXTENDS ALNG PERIPHERY OF INLET LIP IN FORE AND AFT ATTITUDE, AND LATERALLY FLOWING AIR PASSES THROUGH IT. FENCE PRODUCES FINE TURBULENCE AND HIGH VELOCITY AND ENERGY WHICH ENERGIZES THE BOUNDARY LAYER WITHIN THE THROAT AND IMPROVES AIRFLOW TO COMPRESSOR. AT HIGH CRUISE SPEEDS, THE EXCESS AIR ADJACENT TO THE STREAM TUBE FLOWS LATERALLY OUTWARD ACROSS THE INLET LIP AND THE SAME PERFORATE FENCE STRAINS THIS AIRFLOW AND ENERGIZES THE BOUNDARY LAYER ON THE OUTER SURFACE OF THE HOUSING TO DELAY THE DRAG RISE OF THE INLET LIP. IN A STRONG CROSS WIND, THE SAME FENCE ACTS

公开(公告)号：US3534548A

公开(公告)日：1970-10-20

申请号：US3534548D

申请日：1969-06-30

Applicant: AVCO CORP

Inventor： CONNORS HAROLD D

IPC: F02C7/042 ,  F02C7/05 ,  F02C7/04

CPC classification number: F02C7/042 ,  F02C7/05

公开(公告)号：US3400902A

公开(公告)日：1968-09-10

申请号：US52033766

申请日：1966-01-13

Applicant: BEN J. KING

Inventor： KING BEN J

IPC: F02C7/05

CPC classification number: F02C7/05