초록 ▼

Blade assemblies are provided in a number of forms. These blade assemblies may have blades secured to disks (blisk), rings (bling) and drums (blum). The blades and/or the rotor elements formed by these rings, drums or disks can fragment and it is necessary to contain such fragments within a casing.

Blade assemblies are provided in a number of forms. These blade assemblies may have blades secured to disks (blisk), rings (bling) and drums (blum). The blades and/or the rotor elements formed by these rings, drums or disks can fragment and it is necessary to contain such fragments within a casing. Impact energy has a significant effect upon the necessary thickness of the casing to ensure containment. By providing blades as well as rotor elements which incorporate discontinuities which provide flexing under impact, energy is absorbed prior to further fragmentation upon impact engagement with a casing surface; flexing is about the discontinuity. In such circumstances casings may be thinner and therefore significant weight savings achieved with regard to aircraft incorporating gas turbine engines having blade assemblies with discontinuities.

대표청구항 ▼

1. A blade assembly comprising: a rotor element and a plurality of blade elements integrally secured to the rotor element, said rotor element being one of a blisk, a bling, or a blum,said rotor element and at least one of said blade elements enclosing at least one discontinuity therein, the at least

1. A blade assembly comprising: a rotor element and a plurality of blade elements integrally secured to the rotor element, said rotor element being one of a blisk, a bling, or a blum,said rotor element and at least one of said blade elements enclosing at least one discontinuity therein, the at least one discontinuity extending radially and circumferentially across a junction between the rotor element and the at least one blade element to allow intermediate flexing of the respective rotor element and/or blade element upon impact prior to fracture. 2. The assembly as claimed in claim 1 wherein the at least one discontinuity is provided by lack of bonding or fixed association between juxtaposed parts of the blade or rotor element. 3. The assembly as claimed in claim 2 where the lack of bonding is caused by a bond resistant or stop-off material as part of the component manufacture or assembly. 4. The assembly as claimed in claim 1 wherein the at least one discontinuity is provided by a void or slot. 5. The assembly as claimed in claim 1 wherein the at least one discontinuity is provided by a section of material of differing strength than the material from which the rotor element or the blade element is formed. 6. The assembly as claimed in claim 1 wherein the blade elements are bonded to the rotor element. 7. The assembly as claimed in claim 1 wherein a part of the at least one discontinuity extends circumferentially within the rotor element. 8. The assembly as claimed in claim 1 wherein at least one of said rotor element or said blade element is formed from a composite construction comprising a plurality of layers or laminates with discontinuities formed between those layers or laminates. 9. A method of making a blade assembly comprising an integral rotor element and blade elements secured to the rotor element, the rotor element being a blisk (bladed disk) or bling (bladed ring) or blum (bladed drum), said method comprising the steps of: defining a first layer or laminate for the blade assembly, applying a mask incorporating a blank to define at least one discontinuity extending radially and circumferentially across a junction between the rotor element and at least one of the blade elements, applying a second laminate layer to enclose the at least one discontinuity, and applying any further masked layers and laminate layers until a desired blade structure is achieved. 10. The method as claimed in claim 9 further comprising the steps of: retaining the blank within the blade structure to act as a discontinuity. 11. The method as claimed in claim 9 further comprising the steps of: removing the blank within the mask in order to define a void or slot to act as a discontinuity within the blade arrangement. 12. The method as claimed in claim 9 further comprising the steps of: removing the blank in the mask layer and filling the void created with a material of lower strength than the laminate layers to define the discontinuity. 13. A gas turbine engine comprising: an air intake;a propulsive fan;an intermediate pressure compressor;a high pressure compressor;a combustor;a turbine assembly having a high pressure turbine, an intermediate pressure turbine, a low pressure turbine, and an exhaust nozzle; andwherein at least one of said compressor or said turbines includes a blade assembly having an integral rotor element and a plurality of blade elements secured to the rotor element, said rotor element and at least one of said blade elements enclosing at least one discontinuity, the at least one enclosed discontinuity extending radially and circumferentially across a junction of the rotor element and the at least one blade element to allow intermediate flexing of the respective rotor element and/or blade element upon impact prior to fracture.