Multi-layered containment structure for a bladed rotor of a gas turbine engine

An apparatus for a gas turbine engine, comprising:

• a gas turbine engine case extending axially along and circumferentially around an axis;
• the gas turbine engine case comprising a containment structure configured to contain at least one of a blade or a blade fragment from a bladed rotor of the gas turbine engine;
• the containment structure comprising one single and continuous corrugated sheet metal;
• the corrugated sheet metal wrapped two or more times around the axis to provide the containment structure with a multi-layered configuration comprising a first layer of the corrugated sheet metal and a second layer of the corrugated sheet metal;
• and
• a first corrugation in the first layer of the corrugated sheet metal nested in a second corrugation in the second layer of the corrugated sheet metal,
• wherein the gas turbine engine case further comprises a support structure extending axially along and circumferentially around the axis;
• wherein the support structure is configured to support and locate the containment structure within the gas turbine engine;
• wherein the containment structure circumscribes the support structure;
• wherein a section of the corrugated sheet metal forms a housing for the containment structure;
• wherein the housing is attached to the support structure;
• wherein the containment structure is radially between the support structure and the housing, and
• wherein the containment structure and the housing are configured in a monolithic body.

A manufacturing method, comprising:

• forming a containment structure configured to contain at least one of a blade or a blade fragment from a bladed rotor within a gas turbine engine;
• the forming of the containment structure comprising wrapping one single and continuous sheet of metal two or more times around an axis to provide the containment structure;
• and
• attaching the containment structure to a support structure configured to support and locate the containment structure within the gas turbine engine;;
• wrapping a section of the continuous sheet of metal around the containment structure to form a housing;
• and
• the attaching of the containment structure to the support structure comprising attaching the housing to the support structure with the containment structure captured radially between the housing and the support structure,
• wherein:
• a first end of the continuous sheet of metal is bonded to the support structure prior to the wrapping of the continuous sheet of metal;
• a second end of the continuous sheet of metal is radially outboard of and bonded to another portion of the continuous sheet of metal;
• and
• the containment structure and the housing are configured in a monolithic body.