Gas turbine engine compressor casing with internal diameter control

• US 5,017,088 A
• Filed: 12/21/1989
• Issued: 05/21/1991
• Est. Priority Date: 12/21/1988
• Status: Expired due to Fees

• Current Assignee: Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA (Safran SA)
• Original Assignee: Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA (Safran SA)
• Inventors: Miraucourt, Carmen, Delrieu, Gilles L. E.
• Primary Examiner(s): Kwon, John T.
• Assistant Examiner(s): Verdier, Christopher M.
• Application Number:
  US07/454,650
• Time in Patent Office: 516 Days
• Field of Search: 415/214.1, 415/220, 415/108, 415/12, 415/134, 415/135, 415/173.1, 415/173.2, 415/173.3, 415/177, 415/126, 403/28
• US Class Current: 415/173.2
• CPC Class Codes: F01D 11/22 by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
• CPC Class Codes: Y10T 403/21 Utilizing thermal characteristic, e.g. , expansion or contraction, etc.

Abstract

A compressor casing in a gas turbine engine includes an inner jacket formed by two half-shells connected by coupling flanges having cylindrical bellows fitted therebetween and arranged to expand and contract to control the inner diameter of the casing depending on the pressure within the bellows as provided by a supply of air taken from the downstream end of the compressor. The two half-shells are also interconnected by an additional flexible connection.

Claims

1. In a compressor of a gas turbine engine, a casing including at least one radially inner jacket formed by two half-shells provided with coupling flanges, and control means for controlling the inner diameter of the inner jacket depending on the operating conditions of the engine, said control means comprising a plurality of cylindrical bellows secured between said coupling flanges of said two half-shells and connecting said flanges together, said bellows being deformable to vary the length thereof in response to variation of the pressure within said bellows, air bleed ducting communicating said bellows with the air under pressure at the downstream end of the compressor, and further connection means arranged between said two half-shells flexibly securing them together.

2. A compressor casing according to claim 1, wherein said further connection means comprise a plurality of flexible C-shaped connection elements, each of said flexible connection elements straddling a respective one of said bellows and being secured at one end thereof to one of said two half-shells and at the other end thereof to the other of said half-shells.

3. A compressor casing according to claim 2, wherein there are four of each of said bellows and said flexible connection elements.

4. A compressor casing according to claim 1, wherein said casing includes an outer jacket radially outwardly of said inner jacket and said further connection means comprise a number of pairs of lever arms, each of said arms having one end thereof pivotally connected to a respective one of said two half-shells in the vicinity of said coupling flange, and a second end thereof fixed to said outer jacket of the compressor casing by means of an elastic strap.

5. A compressor casing according to claim 4, wherein there are six of each of said bellows and said pairs of lever arms.

6. A compressor casing according to claim 1, including a safety device comprising at least two rods forming spacer struts between said two half-shells for maintaining a minimum inner diameter of said casing.

7. A compressor casing according to claim 1, wherein said casing includes an outer jacket radially outwardly of said inner jacket and walls at each end of said casing whereby a sealed enclosure is formed between said radially inner and outer jackets of said casing, and a valve for controlling the pressure of air within said enclosure.