Turbofan engine

• US 7,721,526 B2
• Filed: 06/28/2006
• Issued: 05/25/2010
• Est. Priority Date: 06/28/2006
• Status: Active Grant

• Current Assignee: Ishikawajima-Harima Heavy Industries Company Limited
• Original Assignee: Ishikawajima-Harima Heavy Industries Company Limited
• Inventors: Imanari, Kuniyuki, Fujimura, Tetsuji, Mizuta, Ikuhisa
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): Nguyen; Andrew
• Application Number:
  US11/427,107
• Publication Number:
  US 20080000216A1
• Time in Patent Office: 1,427 Days
• Field of Search: 602/261, 602/62, 415/143, 415/199.3, 415/199.4, 416/245.R, 416/175, 416/203, 416/198.A, 416/200.A, 416/201.R
• US Class Current: 60/262
• CPC Class Codes: F02K 3/04 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
• CPC Class Codes: F02K 3/06 with front fan

Abstract

A turbofan engine has a fan on a front side thereof and a turbine driving the fan. The turbofan engine includes a disk rotationally driven by the turbine, a spinner detachably mounted at a front side of the disk, a spiral blade integrally mounted on a surface of the spinner, and a rear moving blade detachably mounted on an outer circumferential surface of the disk. The spiral blade and the rear moving blade form a first-stage moving blade of the fan.

Claims

1. A turbofan engine having a fan on a front side thereof and a turbine driving the fan, the turbofan engine further comprising:

a disk rotationally driven by the turbine;

a spinner detachably mounted at a front side of the disk;

a spiral blade integrally mounted on a surface of the spinner, wherein the spiral blade is spirally extended to an axial position of a front end portion of the spinner; and

a rear moving blade detachably mounted on an outer circumferential surface of the disk at the downstream side of the spiral blade;

wherein the spiral blade and the rear moving blade form a first-stage moving blade of the fan,

the spiral blade has a rear end having a first radial height defined with respect to an axis of the engine, and

the rear moving blade has a second radial height, defined with respect to the axis, that is greater than the first radial height.

4. A turbofan engine according to claim 1, further comprising a cushioning member for sealing in a rear end edge portion of the spiral blade and in a front end edge portion close to a base of the rear moving blade.

5. A turbofan engine according to claim 1, further comprising:

a first vibration interfering projection at one or more positions in the rear end portion of the spiral blade; and

a second vibration interfering projection at one or more positions at a front end portion close to a base of the rear moving blade, wherein the second vibration interfering projection collides with the first vibration interfering projection when blade vibration occurring at the spiral blade and the rear moving blade is different therebetween.

8. A turbofan engine according to claim 1 having a hub tip ratio of approximately zero.

10. A turbofan engine according to claim 8, wherein the turbofan engine is a high bypass turbofan engine.

12. A turbofan engine according to claim 1, wherein a concave groove is formed in the rear end surface of the spiral blade, and a protruding portion is provided in the front end surface of the rear moving blade such that the protruding portion enters the concave groove.

2. A turbofan engine having a fan on a front side thereof and a turbine driving the fan, the turbofan engine further comprising:

a disk that is rotationally driven by the turbine and that has an engagement groove extending in an axial direction at a plurality of positions of an outer circumferential portion thereof;

a rear moving blade at the downstream side of the spiral blade, wherein the rear moving blade includes a base portion having a dovetail portion extending in a front-to-rear direction, the dovetail portion is detachably fitted into the engagement groove from a front side;

a spinner detachably mounted at a front side of the disk; and

a spiral blade integrally mounted on a surface of the spinner, wherein the spiral blade is spirally extended to an axial position of a front end portion of the spinner;

wherein the spiral blade and the rear moving blade form a first-stage moving blade of the fan,

the spiral blade has a rear end having a first radial height defined with respect to an axis of the engine, and

the rear moving blade has a second radial height, defined with respect to the axis, that is greater than the first radial height.

3. A turbofan engine according to claim 2, further comprising a retainer integrally provided in a rear end portion of the spinner so that the dovetail portion of the rear moving blade fitted into the engagement groove from the front side is prevented from being displaced to the front side.

6. A turbofan engine according to claim 2, further comprising a cushioning member for sealing in a rear end edge portion of the spiral blade and in a front end edge portion close to a base of the rear moving blade.

7. A turbofan engine according to claim 2, further comprising:

a first vibration interfering projection at one or more positions in the rear end portion of the spiral blade; and

a second vibration interfering projection at one or more positions at a front end portion close to a base of the rear moving blade, wherein the second vibration interfering projection collides with the first vibration interfering projection when blade vibration occurring at the spiral blade and the rear moving blade is different therebetween.

9. A turbofan engine according to claim 2 having a hub tip ratio of approximately zero.

11. A turbofan engine according to claim 9, wherein the turbofan engine is a high bypass turbofan engine.

13. A turbofan engine according to claim 2, wherein a concave groove is formed in the rear end surface of the spiral blade, and a protruding portion is provided in the front end surface of the rear moving blade such that the protruding portion enters the concave groove.