Turbine blade with integral flow meter

Patent metadata

Field	Value
Publication number	US-10683763-B2
Application number	US-201615285347-A
Country	US
Kind code	B2
Filing date	Oct 4, 2016
Priority date	Oct 4, 2016
Publication date	Jun 16, 2020
Grant date	Jun 16, 2020

Abstract

A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes at least one cooling passage defined internally within the turbine blade, and the at least one cooling passage is in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid. The turbine blade also includes at least one flow meter formed within the turbine blade at the inlet that supplies the cooling fluid to the at least one cooling passage.

First claim

What is claimed is:

1. A turbine blade, comprising:
an airfoil extending outwardly from a root, the airfoil having a trailing edge, and a leading edge opposite the trailing edge, the root having a forward side and an aft side;
at least one cooling passage defined internally within the turbine blade, the at least one cooling passage in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid, the inlet defined in the forward side of the root, and the at least one cooling passage comprises at least a first cooling passage defined along the leading edge, at least one trailing cooling passage defined along the trailing edge and a second cooling passage defined between the first cooling passage and the at least one trailing cooling passage, the first cooling passage separated from the second cooling passage by a dividing wall defined within the airfoil;
at least one flow meter defined through the dividing wall downstream of the inlet, the at least one flow meter in fluid communication with the inlet and the second cooling passage, and configured to supply the cooling fluid to the second cooling passage; and
a secondary location defined through the dividing wall downstream of the at least one flow meter in fluid communication with the first cooling passage and the second cooling passage that is configured to supply the cooling fluid to the second cooling passage.

2. The turbine blade of claim 1 , wherein the at least one flow meter is a bore defined through the dividing wall, and the at least one flow meter has a flow meter inlet in fluid communication with the inlet and a flow meter outlet in fluid communication with a second passage inlet of the second cooling passage to supply the second cooling passage with the cooling fluid.

3. The turbine blade of claim 2 , wherein the second cooling passage is a serpentine cooling passage.

4. The turbine blade of claim 2 , wherein the inlet has a first diameter, the at least one flow meter has a second diameter, and the first diameter is greater than the second diameter.

5. The turbine blade of claim 1 , wherein the at least one flow meter is the primary supply of the cooling fluid for the second cooling passage.

6. A method of manufacturing a turbine blade, comprising:
forming the turbine blade with at least one integral cooling passage, the turbine blade including an airfoil extending outwardly from a root, the airfoil having a trailing edge and a leading edge opposite the trailing edge, the root having a forward side and an aft side, the at least one cooling passage defined internally within the turbine blade, the at least one cooling passage having an inlet in fluid communication with a source of a cooling fluid, the inlet defined in the forward side of the root, and the at least one cooling passage comprises at least a first cooling passage defined along the leading edge, at least one trailing cooling passage defined along the trailing edge and a second cooling passage defined between the first cooling passage and the at least one trailing cooling passage, the first cooling passage separated from the second cooling passage by a dividing wall defined within the airfoil; and
machining at least one flow meter through the dividing wall downstream of the inlet to adjust a flow of the cooling fluid into the second cooling passage based on a determined cooling requirement for the second cooling passage, the at least one flow meter in fluid communication with the inlet and the second cooling passage to supply the cooling fluid to the second cooling passage, and the dividing wall including a secondary location defined through the dividing wall downstream of the at least one flow meter in fluid communication with the first cooling passage and the second cooling passage to supply the cooling fluid to the second cooling passage.

7. The method of claim 6 , wherein the forming the turbine blade further comprises:
forming the second cooling passage as a serpentine cooling passage, and the at least one flow meter is the primary supply of the cooling fluid to the serpentine cooling passage.

8. A turbine blade, comprising:
an airfoil extending outwardly from a root, the airfoil having a trailing edge, a leading edge opposite the trailing edge, the root having a forward side opposite an aft side;
at least a first cooling passage, a second cooling passage and at least a trailing cooling passage defined internally within the turbine blade, the first cooling passage in fluid communication with a source of cooling fluid via an inlet defined in the turbine blade to receive a cooling fluid, the first cooling passage defined along the leading edge, the at least one trailing cooling passage defined along the trailing edge and the second cooling passage defined between the first cooling passage and the at least one trailing cooling passage, the first cooling passage separated from the second cooling passage by a dividing wall defined within the airfoil, and the inlet is defined in the forward side of the root;
at least one flow meter defined through the dividing wall downstream of the inlet, the at least one flow meter has a flow meter inlet in fluid communication with the inlet and a flow meter outlet in fluid communication with a second passage inlet of the second cooling passage, and the at least one flow meter is configured to supply the cooling fluid to the second cooling passage; and
a secondary location defined through the dividing wall downstream of the at least one flow meter in fluid communication with the first cooling passage and the second cooling passage that is configured to supply the cooling fluid to the second cooling passage.

9. The turbine blade of claim 8 , wherein the at least one flow meter is the primary supply of the cooling fluid to the second cooling passage, the at least one flow meter is configured to supply at least 60% of the cooling fluid to the second cooling passage and the secondary location is configured to supply up to 40% of the cooling fluid to the second cooling passage.

10. The turbine blade of claim 8 , wherein the at least one flow meter is a bore defined through the dividing wall.

11. The turbine blade of claim 8 , wherein the second cooling passage is a serpentine cooling passage.

Assignees

• Honeywell Int Inc

Inventors

• Halfmann Steve
• Crites Daniel C
• Kahrs Michael
• Riahi Ardeshir
• Miller Jude

Classifications

• F01D5/081 Primary

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2230/61

  using limited numbers of standard modules which can be adapted by machining · CPC title

• F01D5/188

  with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall · CPC title

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title