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US 2014/0109548 A1Published application
High pressure rotor disk
AssigneeUnited Technologies Corporation
InventorScott D. Virkler
Life of this patent
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Abstract
A rotor disk for a gas turbine engine is disclosed and formed to enable operation at high rotational speeds in a high temperature environment. The rotor disk is formed to include a bore, a live rim diameter and an outer diameter related to each other according to defined relationships.
Claims24
A gas turbine engine comprising:
- a compressor section including a high pressure compressor and a low pressure compressor;
- a combustor in fluid communication with the compressor section;
- a turbine section in fluid communication with the combustor, wherein the turbine section includes a high pressure turbine driving the high pressure compressor and a low pressure turbine driving the low pressure compressor, wherein at least one of the high pressure turbine and the high pressure compressor includes a disk having a bore diameter (D) related to a bore width (W) according to a ratio (D/W) between about 1.25 and about 1.65.
A rotor disk for a gas turbine engine comprising:
- an outer diameter (OD) related to a bore diameter (D) according to a ratio (OD/D) that is between about 2.95 and about 3.25.
A method of fabricating a rotor disk for a gas turbine engine comprising;
- forming a bore including a bore diameter (D) and a live rim diameter (d) with a ratio (d/D) of the live rim diameter (d) to the bore diameter (D) being between about 2.25 and about 3.00
- forming at least one lug for mounting a blade at a live rim diameter (d);
- and
- forming an outer diameter (OD).
1 more element
Dependencies are inferred from the claim text.