Turbine blade for a gas turbine engine

USD1148007SActive Publication Date: 2026-09-15SIEMENS ENERGY GLOBAL GMBH & CO KG
View PDF 11 Cites 0 Cited by

Patent Information

Application Number
US29/999996
Authority / Receiving Office
US · United States
Patent Type
Designs(United States)
Current Assignee / Owner
Filing Date
2025-04-18
Publication Date
2026-09-15
Estimated Expiration
2041-09-15

Smart Images

  • Figure USD1148007-D00000_ABST
    Figure USD1148007-D00000_ABST
Patent Text Reader
Need to check novelty before this filing date? Find Prior Art

Description

[0001] FIG. 1 is a perspective view of a turbine blade for a gas turbine engine showing the new design.

[0002] FIG. 2 is a left side view of the turbine blade for a gas turbine engine of FIG. 1.

[0003] FIG. 3 is a right side view of the turbine blade for a gas turbine engine of FIG. 1

[0004] FIG. 4 is a front view of the turbine blade for a gas turbine engine of FIG. 1.

[0005] FIG. 5 is a rear view of the turbine blade for a gas turbine engine of FIG. 1.

[0006] FIG. 6 is a top view of the turbine blade for a gas turbine engine of FIG. 1.

[0007] FIG. 7 is a bottom view of the turbine blade for a gas turbine engine of FIG. 1.

[0008] FIG. 8 is an enlarged perspective view of a portion of the turbine blade for a gas turbine engine of FIG. 1.

[0009] FIG. 9 is a left side view of the portion of the turbine blade for a gas turbine engine of FIG. 8.

[0010] FIG. 10 is a right side view of the portion of the turbine blade for a gas turbine engine of FIG. 8

[0011] FIG. 11 is a front view of the portion of the turbine blade for a gas turbine engine of FIG. 8.

[0012] FIG. 12 is a rear view of the portion of the turbine blade for a gas turbine engine of FIG. 8.

[0013] FIG. 13 is a top view of the portion of the turbine blade for a gas turbine engine of FIG. 8; and,

[0014] FIG. 14 is a bottom view of the portion of the turbine blade for a gas turbine engine of FIG. 8.

[0015] The elements shown in broken lines are included for the purpose of illustrating environment and form no part of the claimed design.

Claims

The ornamental design for a turbine blade for a gas turbine engine as shown and described.

Citation Information

Patent Citations

  • Gas turbine engine airfoil

    US20100074759A1

  • Scaling to custom-sized turbomachine airfoil method

    US20150089809A1

  • Squealer shelf airfoil tip

    US20190368359A1

  • Second stage turbine blade

    US20200063570A1

  • Additively manufactured core

    US20200101525A1