US 12,359,569 B2
Turbine blade tip cooling hole supply plenum
Leissner F. Poth, III, San Antonio, TX (US); Sanjay S. Hingorani, Johns Creek, GA (US); and Bensy Samuel, Alpharetta, GA (US)
Assigned to Mechanical Dynamics and Analysis LLC, Latham, NY (US)
Filed by Mechanical Dynamics and Analysis LLC, Latham, NY (US)
Filed on Nov. 1, 2023, as Appl. No. 18/499,831.
Application 18/499,831 is a division of application No. 17/196,523, filed on Mar. 9, 2021, granted, now 11,840,940.
Prior Publication US 2024/0060420 A1, Feb. 22, 2024
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/187 (2013.01) [F05D 2220/32 (2013.01); F05D 2230/80 (2013.01); F05D 2240/307 (2013.01); F05D 2250/74 (2013.01); F05D 2260/20 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A turbine blade comprising:
a root defining a plurality of supply channels configured to receive a supply of pressurized gas;
a blade tip defining a plurality of tip cooling apertures open through a pressure side surface of the blade tip; and
an airfoil extending in a radially outward direction from the root to the blade tip, the airfoil having a pressure side surface and a suction side surface connected to the pressure side surface of the airfoil by a leading edge of the airfoil and a trailing edge of the airfoil,
wherein the turbine blade defines a first serpentine interior cooling passage having a first leg, a second leg, a third leg, a first junction portion, and a second junction portion, the first leg configured to receive pressurized gas from at least one supply channel of the plurality of supply channels, the first leg extending radially within the airfoil and connected to the second leg by the first junction portion proximate the blade tip, the second leg extending radially between the first junction portion and the second junction portion, the second junction portion connecting the second leg to the third leg, the third leg extending radially from the second junction portion toward the blade tip,
wherein the plurality of tip cooling apertures includes a forward tip cooling aperture that has a forward end that opens into the first junction portion and an aftward end that opens through the pressure side surface of the blade tip at a location that is radially outward of the third leg and axially aftward of at least a portion of the third leg,
wherein the first junction portion includes a plenum that overlaps the third leg in an axial direction of the turbine blade, the plenum having a width that narrows in the axial direction aftward of the portion of the third leg,
wherein the airfoil comprises a nominal airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table I, wherein the values of X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each value of Z which is a distance expressed as a percentage of a span of the nominal airfoil profile, the airfoil profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.