Contra-rotating fan engine

• US 5,103,635 A
• Filed: 09/07/1990
• Issued: 04/14/1992
• Est. Priority Date: 09/27/1989
• Status: Expired due to Fees

• Current Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Original Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation
• Inventors: Lardellier, Alain M. J.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): RICHMAN, HOWARD
• Application Number:
  US07/578,675
• Time in Patent Office: 585 Days
• Field of Search: 60/39.162, 60/268, 60/226.1, 60/226.2, 60/226.3, 415/77, 415/79, 415/191, 416/129
• US Class Current: 60/226.1
• CPC Class Codes: F02C 3/067 having counter-rotating rotors F02C3/073 takes precedence
• CPC Class Codes: F02K 3/072 with counter-rotating , e.g. fan rotors
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine intended for use as an aircraft engine which includes a gas generator which supplies interdigitated, contra-rotating radially inner and outer low-speed power turbines driving forward mounted contra-rotating front and rear fans, the gases flowing through the gas generator from the rear of the engine towards the front, and then flowing in a rearward direction through the power turbines. The front fan is driven by the radially inner power turbine via a central shaft extending towards the front of the engine and supporting a disc carrying the front fan, and the rear fan is driven by the radially outer power turbine via a forwardly extending drum which is rotatably mounted between the central shaft and a stationary structure of the engine and which carries the rear fan. This structure permits the pod mounting of a high by-pass ratio engine under wing of an aircraft.

Claims

1. A gas turbine engine for use as an aircraft engine and having front and rear ends defined in relation to the direction of travel of an aircraft propelled by said engine, including:

an outer casing;

air intake means including a plurality of ducts arranged within said outer casing and an annular chamber for receiving said intake air from said ducts;

a gas generator disposed to received said intake air from said annular chamber and comprising

compression stages,

a combustion chamber, and

turbine stages for driving said compression stages, said annular chamber being located to the rear of said gas generator and said generator being arranged such that said intake air travels in a forward direction successively through said compression stages, said combustion chamber, and said turbine stages thereof;

a forwardly extending axial duct extending from said gas generator;

interdigitated, contra-rotating radially inner and outer low-speed power turbines disposed radially outwards of and in communication with said axial duct;

means connected to said axial duct for receiving gases conducted thereby from said gas generator and reversing the direction of flow of said gases to feed said gases in a rearward primary flow direction through said power turbines to drive said turbines;

two forward mounted contra-rotating fans arranged one in front of the other to define a front fan and a rear fan;

means drivingly interconnecting said radially inner power turbine to said front fan, said means including

a central shaft connected to said inner power turbine and extending towards the front of said engine, and

means supporting said front fan on said central shaft;

means drivingly interconnecting said radially outer power turbine to said rear fan, said means including

a forwardly extending drum connected to said outer power turbine and rotatably mounted around said central shaft, and

means supporting said rear fan on said drum;

wherein the disposition of said engine comprises, in succession from front to rear;

said front fan;

said rear fan which is radially disposed about part of said air intake means;

said interdigitated power turbines which are radially disposed about said axial duct from said gas generator;

said gas generator turbine stages;

said combustion chamber;

said gas generator compressor stages; and

said annular chamber of said air intake means, wherein said engine includes a conical first structural ring surrounding said power turbines and having a cylindrical end portion forward thereof, and a second structural ring positioned at least partially within the rear end of said power turbines, the assembly including said rear fan and said radially outer power turbine connected thereto being rotatably mounted at the front by means of a bearing disposed on the inside of aid cylindrical end portion of said first structural ring and at the rear by means of a bearing carried by the downstream inner end of said outer power turbine and disposed outside of said second structural ring.

2. A gas turbine engine according to claim 1, wherein said rear fan includes a base platform and a second platform disposed radially outwards of said base platform and arranged to form a forward extension of said outer casing of said engine, said platforms defining therebetween said part of said air intake means.

3. A gas turbine engine according to claim 1, wherein each of said fans includes an outer ring for ducting a secondary flow of said engine.

4. A gas turbine engine according to claim 1, wherein said fans are each provided with a blade-pitch changing mechanism.

5. A gas turbine engine according to claim 3, wherein each of said fans has a fixed blade pitch, and the forward part of said outer casing of said engine is provided with deformable means for modifying the output cross-section of the secondary flow path of said engine.

6. A gas turbine engine according to claim 5, wherein said deformable means comprises an annular assembly of first flaps hingedly connected at an edge portion thereof to said outer casing, actuator means for moving said first flaps, and second flaps hingedly connected to said first flaps and movable thereby.

7. A gas turbine engine according to claim 3, wherein said outer casing includes secondary flow direction reversal panels hingedly mounted at their downstream edge, and actuators for rotating said panels about said hinged downstream edges.

8. A gas turbine engine according to claim 1, wherein the assembly consisting of said front fan and said radially inner power turbine connected thereto is rotatably mounted at the front by means of a bearing disposed between said central shaft and said drum supporting said rear fan, and at the rear by means of a bearing disposed between said second structural ring and a bearing surface at the downstream end of said inner power turbine.

9. A gas turbine engine according to claim 3, wherein the blades of said front fan carry a intermediate ring at about the mid-height position of said blades dividing said fan into inner and outer sections, and said front fan comprises additional blades between said intermediate ring and said outer ring to provide said outer section with twice a many blades as said inner section.