Lateral turbojet improved in order to limit the deformation thereof

Patent metadata

Field	Value
Publication number	US-9366186-B2
Application number	US-201113813071-A
Country	US
Kind code	B2
Filing date	Jul 15, 2011
Priority date	Jul 30, 2010
Publication date	Jun 14, 2016
Grant date	Jun 14, 2016

Abstract

A turbojet includes an intermediate casing outer shroud connected to a front suspension and a primary structure connected to a rear suspension; the shroud and the primary structure are held in a coaxial relationship by arms with at least some of the arms being shaped and/or arranged to deform in response to thrust from the turbojet by creating a deforming torque between the shroud and the primary structure in opposition to opposing stress generated by the thrust.

First claim

The invention claimed is:

1. A two-stream turbojet for attaching laterally to a fuselage of an airplane via two longitudinally spaced apart suspensions including a front suspension and a rear suspension, the turbojet comprising:
an intermediate casing outer shroud attached to the front suspension; and
a propulsion primary structure attached to the rear suspension;
the intermediate casing outer shroud and the propulsion primary structure being held in a coaxial relationship by a set of arms, each arm including a right section that is hollow and being fastened by ends thereof to the intermediate casing outer shroud and to the propulsion primary structure; and
wherein at least some of the arms include a C-shaped right section defined by a slot extending from the intermediate casing outer shroud to the propulsion primary structure,
wherein in response to thrust from the turbojet, the C-shaped right section creates a deforming torque between the intermediate casing outer shroud and the propulsion primary structure, the deforming torque having a direction opposite to a bending moment that is generated under effect of the turbojet thrust by a force reaction couple at a thrust axis and the front suspension.

2. The turbojet according to claim 1 , wherein the at least some of the arms are shaped and/or arranged to provide coupling between shear and twisting so that a center of torsion of a right section of the at least some of the arms is situated outside a midplane of the respective arm, on a side towards an opposite direction from the front suspension relative to the midplane.

3. The turbojet according to claim 1 , wherein the slot is closed by an elastomer seal.

4. The turbojet according to claim 1 , wherein certain arms extend radially in line with attachment points of the front suspension, and other arms extend parallel to a radius of the propulsion primary structure and the other arms are located, with respect to the radius, on a side towards an opposite direction from attachment points of the front suspension.

5. An intermediate casing comprising the intermediate casing outer shroud and arms configured to connect the intermediate casing outer shroud to the primary propulsion structure, the intermediate casing being arranged for fitting to a turbojet according to claim 1 .

6. A two-stream turbojet for attaching laterally to a fuselage of an airplane by two longitudinally spaced apart suspensions including a front suspension and a rear suspension, the turbojet comprising:
an intermediate casing outer shroud attached to the front suspension and a propulsion primary structure attached to the rear suspension;
the intermediate casing outer shroud and the propulsion primary structure being held in a coaxial relationship by a set of arms, each arm being fastened via ends thereof to the intermediate casing outer shroud and to the propulsion primary structure; and
wherein at least one of the arms is parallel and offset from a plane passing through a center axis of the propulsion primary structure to create a deforming torque between the intermediate casing outer shroud and the propulsion primary structure, the deforming torque having a direction opposite to a bending moment that is generated under effect of the turbojet thrust by a force reaction couple at a thrust axis and the front suspension.

7. The turbojet according to claim 6 , wherein the at least one arm extends parallel to a corresponding radial direction on an other side of the radial direction relative to the plane on a side toward an opposite direction from attachment points of the front suspension, and wherein other arms of the set of arms extend radially in line with the attachment points of the front suspension.

8. The turbojet according to claim 6 , wherein each of the arms includes a right section that is hollow.

9. The turbojet according to claim 6 , wherein the arms include a right section that is symmetrical and closed.

10. A two-stream turbojet for attaching laterally to a fuselage of an airplane via two longitudinally spaced apart suspensions including a front suspension and a rear suspension, the turbojet comprising:
an intermediate casing outer shroud attached to the front suspension; and
a propulsion primary structure attached to the rear suspension;
the intermediate casing outer shroud and the propulsion primary structure being held in a coaxial relationship by a set of arms, each arm including a right section that is hollow and being fastened by ends thereof to the intermediate casing outer shroud and to the propulsion primary structure; and
wherein at least some of the arms include an approximately trapezoidal right section defined by a narrow side and an opposite wide side extending from the intermediate casing outer shroud to the propulsion primary structure, wherein the narrow side is located, with respect to the opposite wide side, towards attachment points of the front suspension,
wherein in response to thrust from the turbojet, the approximately trapezoidal right section creates a deforming torque between the intermediate casing outer shroud and the propulsion primary structure, the deforming torque having a direction opposite to a bending moment that is generated under effect of the turbojet thrust by a force reaction couple at a thrust axis and the front suspension.

11. The turbojet according to claim 10 , wherein the at least some of the arms are associated with respective fairings for improving streamlining thereof.

12. The turbojet according to claim 10 , wherein the at least some of the arms are shaped and/or arranged to provide coupling between shear and twisting so that a center of torsion of a right section of the at least some of the arms is situated outside a midplane of the respective arm, on a side opposite on a side towards an opposite direction from the front suspension relative to the midplane.

13. The turbojet according to claim 10 , wherein certain arms extend radially in line with attachment points of the front suspension, and other arms extend parallel to a radius of the propulsion primary structure and the other arms are located, with respect to the radius, on a side towards an opposite direction from the attachment points of the front suspension.

Assignees

• Bellabal Francois Robert
• Snecma

Inventors

• Bellabal Francois Robert

Classifications

• F02K1/82

  Jet pipe walls, e.g. liners · CPC title

• B64D27/20

  within, or attached to, fuselages · CPC title

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F02K1/80

  Couplings or connections · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title