System and method for removing or installing the hot section of a gas turbine engine

A method of removing an engine module from a gas turbine engine, wherein the gas turbine engine includes a compressor section, a combustor, a turbine section, an engine shaft that is engaged with the compressor section and the turbine section and extends along an axial centerline of the engine, and an engine casing having a first engine casing segment and a second engine casing segment that are axially separable from one another, wherein the method comprises:

• providing a plurality of rail and guide block assemblies, wherein each rail and guide block assembly of the plurality of rail and guide block assemblies includes a rail head, a rail, and a guide block, wherein within each rail and guide block assembly the rail is fixedly attached to the rail head and extends axially out from the rail head;
• attaching the rail head of each rail and guide block assembly to the first engine casing segment so that an axial length of the rail is disposed parallel to the axial centerline of the engine;
• attaching the guide block of each rail and guide block assembly to the second engine casing segment so that the rail is received within an aperture disposed in the guide block, and the rail is disposed in the guide block in a manner that permits linear traverse of the rail relative to the guide block;
• wherein the engine module is attached to the first engine casing segment;
• and
• removing the engine module from the gas turbine engine by axially translating the first engine casing segment from the second engine casing segment with the plurality of rail and guide block assemblies guiding the axial translation;
• wherein the plurality of rail and guide block assemblies includes more than two rail and guide block assemblies of the plurality of rail and guide block assemblies, and the rail and guide block assemblies are equidistantly spaced apart from one another around a circumference of the engine casing.

A method of installing an engine module into a gas turbine engine, wherein the gas turbine engine includes a compressor section, a combustor, a turbine section, an engine shaft that is engaged with the compressor section and the turbine section and extends along an axial centerline of the engine, and an engine casing having a first engine casing segment and a second engine casing segment that are axially separable from one another, wherein the method comprises:

• providing a plurality of rail and guide block assemblies, wherein each rail and guide block assembly of the plurality of rail and guide block assemblies includes a rail head, a rail, and a guide block, wherein within each rail and guide block assembly the rail is fixedly attached to the rail head and extends axially out from the rail head;
• attaching the rail head of each rail and guide block assembly to the first engine casing segment;
• attaching the guide block of each rail and guide block assembly to the second engine casing segment;
• wherein the engine module is attached to the first engine casing segment;
• disposing the rail of each rail and guide block assembly into the guide block of that respective rail and guide block assembly;
• and
• axially translating the first engine casing segment and attached engine module into engagement with the second engine casing segment guided by the plurality of rail and guide block assemblies;
• wherein the plurality of rail and guide block assemblies includes more than two rail and guide block assemblies of the plurality of rail and guide block assemblies, and the rail and guide block assemblies are equidistantly spaced apart from one another around a circumference of the engine casing.