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US 10,309,232 B2Granted
Gas turbine engine with stage dependent material selection for blades and disk
AssigneeUnited Technologies Corporation
InventorsFrederick M. Schwarz, Daniel Bernard Kupratis
Life of this patent
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Abstract
A gas turbine engine includes a shaft defining an axis of rotation and a fan driving turbine configured to drive the shaft. The fan driving turbine comprises a plurality of stages that are spaced apart from each other along the axis. Each stage includes a turbine disk comprised of a disk material and a plurality of turbine blades comprised of a blade material. The disk material and the blade material for one of the plurality of stages is selected based on a location of the one stage relative to the other stages of the plurality of stages.
Claims28
A gas turbine engine comprising:
- at least a first shaft and a second shaft rotating at a higher speed than the first shaft, wherein the first and second shafts rotate about an engine axis of rotation;
- a geared architecture coupling the first shaft to a fan;
- at least a first driving turbine configured to drive the first shaft and a second driving turbine to drive the second shaft, wherein the first driving turbine is positioned downstream of the second driving turbine such that the second driving turbine comprises a high pressure turbine and the first driving turbine comprises a low pressure turbine;
- a combustor positioned immediately upstream of the second driving turbine;
- and
- wherein the low pressure turbine comprises a plurality of stages including at least a first turbine stage and a second turbine stage spaced immediately aft of the first turbine stage along the axis, wherein the first turbine stage has a first temperature capability that is higher than a second temperature capability of the second turbine stage, and wherein each of the first and second turbine stages of the low pressure turbine are comprised of:
- a turbine disk comprised of a disk material;
- and
- a plurality of turbine blades comprised of a blade material, wherein the disk material for at least one of the first and second turbine stages is different than the blade material for the at least one of the first and second turbine stages, and
- wherein the disk material and the blade material for the first and second turbine stages are selected independently of each other based on operational temperatures at each stage's respective location along the first shaft of the first and second turbine stages.
7 more elements
A gas turbine engine comprising:
- at least a first shaft and a second shaft rotating at a higher speed than the first shaft, wherein the first and second shafts rotate about an engine axis of rotation;
- a geared architecture coupling the first shaft to a fan;
- at least a first driving turbine configured to drive the first shaft and a second driving turbine to drive the second shaft, wherein the first driving turbine is positioned downstream of the second driving turbine such that the second driving turbine comprises a high pressure turbine and the first driving turbine comprises a low pressure turbine;
- a combustor positioned upstream of the second driving turbine;
- and
- wherein the low pressure turbine comprises a plurality of turbine stages including at least a first turbine stage and a second turbine stage spaced immediately aft of the first turbine stage along the axis,
- wherein the first turbine stage includes a first disk comprised of a first disk material having a first disk temperature capability and a first set of blades comprised of a first blade material having a first blade temperature capability,
- wherein the second turbine stage includes a second disk comprised of a second disk material different from the first disk material and having a second disk temperature capability, and a second set of blades comprised of a second blade material different from the first blade material and having a second blade temperature capability, and
- wherein the first disk temperature capability is higher than the second disk temperature capability and the first blade temperature capability is higher than the second blade temperature capability.
6 more elements
A gas turbine engine comprising:
- at least a first shaft and a second shaft rotating at a higher speed than the first shaft, wherein the first and second shafts rotate about an engine axis of rotation;
- a geared architecture coupling the first shaft to a fan;
- at least a first driving turbine configured to drive the first shaft and a second driving turbine to drive the second shaft, wherein the first driving turbine is positioned downstream of the second driving turbine such that the second driving turbine comprises a high pressure turbine and the first driving turbine comprises a low pressure turbine;
- a combustor positioned upstream of the second driving turbine;
- and
- wherein the low pressure turbine comprises a plurality of turbine stages including at least a first turbine stage, a second turbine stage spaced immediately aft of the first turbine stage along the axis, and a third turbine stage spaced immediately aft of the second turbine stage along the axis,
- wherein the first turbine stage includes a first disk comprised of a first disk material having a first disk temperature capability and a first set of blades comprised of a first blade material having a first blade temperature capability,
- wherein the second turbine stage includes a second disk comprised of a second disk material having a second disk temperature capability and a second set of blades comprised of a second blade material having a second blade temperature capability,
- wherein the third turbine stage includes a third disk comprised of a third disk material having a third disk temperature capability and a third set of blades comprised of a third blade material having a third blade temperature capability,
- wherein the first, second, and third disk materials comprises at least two different materials,
- wherein the first, second, and third blade materials comprises at least two different materials, and
- wherein the first and second disk temperature capability is higher than the third disk temperature capability and the first and second blade temperature capability is higher than the third blade temperature capability.
9 more elements
Dependencies are inferred from the claim text.