US 12,270,315 B2
Rotor blade for a turbomachine, associated turbine module, and use thereof
Karl Maar, Munich (DE); Joerg Frischbier, Munich (DE); and Hans-Peter Hackenberg, Munich (DE)
Assigned to MTU AERO ENGINES AG, Munich (DE)
Appl. No. 17/597,674
Filed by MTU Aero Engines AG, Munich (DE)
PCT Filed Jul. 14, 2020, PCT No. PCT/DE2020/000155
§ 371(c)(1), (2) Date Jan. 18, 2022,
PCT Pub. No. WO2021/013281, PCT Pub. Date Jan. 28, 2021.
Claims priority of application No. 102019210693.5 (DE), filed on Jul. 19, 2019.
Prior Publication US 2022/0259977 A1, Aug. 18, 2022
Int. Cl. F01D 5/14 (2006.01); F01D 5/28 (2006.01); F04D 29/32 (2006.01)
CPC F01D 5/141 (2013.01) [F01D 5/147 (2013.01); F01D 5/288 (2013.01); F04D 29/324 (2013.01); F05D 2220/36 (2013.01); F05D 2240/301 (2013.01); F05D 2260/941 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A rotor blade wherein the rotor blade is configured and arranged in a gas duct of a turbomachine and comprises a rotor blade airfoil wherein
the rotor blade has a blade root, an inner shroud, and an outer shroud,
radially inwardly has a chord length Si, the chord length Si being taken in a tangential section directly above the blade root or the inner shroud,
radially outwardly has a chord length Sa, the chord length Sa being a tangential section directly below the outer shroud, and,
a radial position rx, between radial positions of the tangential sections of the chord length Si and the chord length Sa, has a chord length Sx,
the chord length Sx in the radial position rx being greater than or equal to the chord length Si radially inwardly (Si≤Sx), and
the chord length Sa radially outwardly being less than or equal to 0.9 times the chord length Sx in the radial position rx (Sa≤0.9 Sx).